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Aero Troll - Hegedus Aerodynamics

1. HEFHHHH beginning of NACA RM L50H08 mid body py script import math from examples NACA RM L50H08 Scripts import NACA RM L50H08 92 reload NACA_RM_L50H08 def ssT oPt ssx sSy pp NACA RM L50H08 midBodySSToPt ssx ssy pp Lir EEE ending of NACA RM L50H08 mid body py script beginning of NACA RM L50H08 aft body py script import math from examples NACA RM L50H08 Scripts import NACA RM L50H08 reload NACA RM L50H08 def ssToPt ssx ssy pp NACA RM L50H08 aftBodySSToPt ssx ssy pp TERES HEHEHEH import ending of NACA RM L50H08 aft body py script beginning of NACA RM L50H08 wing py script math from examples NACA RM L50H08 Scripts import NACA RM L50H08 reload NACA RM L50H08 def ssToPt ssx ssy pp NACA RM L50H08 wingSSToPt ssx ssy pp HEEEEE ending of NACA RM L50H08 wing py script 93
2. HE Cubic Spline method Based on spline method from Numerical Methods for Engineers Second Edition d Steven C Chapra Raymond P Canale ef CubicSpline xx yy dd fDY1DX fDYNDX get number of points mm len xx create the arrays for the tridiagonal system aa 0 mm bb 0 mm cc 0 mm set values for ii in range 1 mm 1 aa ii x ii xx ii 1 ia 2 0 xx ii 1 xx ii 11 c ii x ii 1 xx i i ii 6 0 yylii 1 yylii xx ii 1 xx ii yy ii yy ii 1 xx ii xx ii 1 set first values if fDY1DX 0 set starting first derivative to zero aa 0 0 0 bb 0 2 0 cc 0 1 0 dd 0 6 0 yy 1 yy 0 xx 1 xx 0 xx 1 xx 0 else set starting second derivative to zero aa 0 0 0 bb 0 1 0 cc 0 0 0 dd 0 0 0 set last values if fDYNDX 0 aa mm 1 bb mm 1 cc mm 1 dd mm 1 else set acne second derivative to zero aa mm 1 bb mm 1 cc mm 1 set ending first derivative to zero SV ENNIO WoH g CI EZ Laz ec 88 yy mm 1 yy mm 2 xx mm 1 xx mm 2 xx mn 1 xx mm 2 dd mm 1 0 0 solve TriDiag aa bb cc dd end of cubic spline method Cublic Spline Evaluation method Based on spline method from Numerical Methods for Engineers Second Edition d Steven C Chapra Raymond P Canale ef CubicSplineYY xin xx yy dd get numb
3. Inc Base Load Seg 1 Theta 90 0 Include Body Theta Panels 6 Delete Segment 1 Seg 2 Theta 270 0 Include Body Theta Panels 6 Delete Segment 2 Accept Accept AII Revert Revert All TT Next select the Accept button and the top and side views should look like the following two figures File Edit View Help Components o 5 Nose Body o CY Fin Set o 5 Body 78 Aero Troll v0 2 0b File Edit View Help Components gt 5 Nose Body o 5 Fin Set gt 7 Body For the wind tunnel model in TM 2001 210652 the body internal diameter was beveled to the outer diameter at the base of the model to allow the internal pressures to act over the entire base area Also the Ca due to cavity pressures was subtracted from the measured balance C4 Therefore to mimic this in the Aero Troll model the Inc Base Load for the Body component is unselected This completes the geometry buildup for this example Wing T Tail The following example is of a generic wing body tee tail configuration This geometry is made up of one Nose Body component three Fin Set components and one Body component After creating an AT Analysis component create a Nose Body component with the following parameters Include Wake Unselected Nose Type Ogive Nose Length 3 5 Body Length 1 5 Base Panels 0 79 The Base Pa
4. Inc Base Load If selected the base will not be used in the calculation of the aerodynamic loads More Display the advanced settings dialog 33 The following input parameters are for a nose segment Each nose segment represents a set of panels laid out along a portion of the circumference The segments are then connected side edge to side edge to loop over the circumference of the nose The total number of panels along the circumference of the body is the sum of the number of panels in each segment Each segment will be represented by a panel network for a PANAIR analysis Theta The ending circumferential theta location for the segment The segment will start at the ending theta of the previous segment For the first segment the starting theta is the ending theta of the last segment The ending theta location must not match the ending theta location of any other segment A theta value of zero represents the top of the body The theta value is positive in a clockwise direction when viewed from the back towards the front The value is in degrees Include Body If unselected panels will not be laid out along the circumference Theta Panels The number of panels in the theta direction for this segment The value must be greater than zero Body The Body component is a circular geometry After executing the analysis method for this component the final integrated loads and moments are shown in the results panel of the base componen
5. 0 pp 1 radius pp 2 0 0 else angle ssy math pi pp i radius math cos angle pp 2 radius math sin angle end of aftBodySSToPt method 90 beginning of wingSSToPt method def wingSSToPt ssx ssy pp get root value if ssx 0 0 wxl xx1A wyl yy1A elif ssx 1 0 wxl xx1B wyl yy1B else wxl xx1A ssx xx1B xx1A wyl 40 CubicSplineYY wx1 40 xl rl dl get tip value if ssx 0 A05 wx2 xx2A wy2 yy2A elif ssx 1 0 wx2 xx2B wy2 yy2B else wx2 xx2A ssx xx2B xx2A wy2 yy2A ssx yy2B yy2A set values if ssy 0 0 pp 0 wx1 pp 1 wyl elif ssy 1 0 pp 0 wx2 pp 1 wy2 else pp 0 p 1 pp 2 h m i wxl ssy wx2 wx1 wyl ssy wy2 wyl 0 ol I end of wingSSToPt method oH set up global values define body shape xl 0 0000 0050 0075 0125 0250 0500 0750 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8333 8500 9000 9500 0000 00000 00231 00298 00428 00722 01205 01613 01971 02593 03090 03465 El I OMS QOO O00 ASS PERO SO DOG OSSO GS OS OS GO COCO 0 03741 0 03933 0 04063 0 04143 0 04167 0 04130 0 04024 0 03842 0 03562 0 03128 0 02526 0 02083 0 01852 0 01125 0 00439 0 00000 0 len x1 dl L create slpine for body shape CubicSpline
6. 6 Box 7 Panel 8 Ground Plane 9 Field Pts 10 Coordinate System 11 Group The catalog of components will be expanded in upcoming releases For this example a Nose Body component is created with the approach given above After the component has been selected from the Add menu a dialog box will appear requesting a name for the component The default can be accepted or a new name entered The Rename menu item of the component popup menu can be used to rename 10 the component at a later time Once the component is created it will be shown in the Main Display panel assuming the AT Analysis component is active active base components are described in the Views section below After the component is created the component parameters can be modified by editing the component To edit the component right click on the Nose Body component node and select the Edit menu item in the component popup menu This is shown below File Edit View Help Components NOS Road Cut Copy Paste Delete Edit Rename R Hide Analysis Type gt Results 11 Once the Edit menu item is selected the Edit window with an Edit panel for the Nose Body component will be displayed This is shown below Edit Window DOR Do Shirt 0 0 Tht Rot Include Wake Local Wake Ll Nose Type 8 Cone Ogive Nose Radius es Nose Length be l Body Length bo ed Tip Radius Nose
7. Droop bo Tip Panels h Accept acceptan Revert 05 20 30 0 0 0 0 E 12 To modify the component change an entry in one of the text fields or change the selection of a check box or radio button Once all the modifications have been made select the Accept button to update the component with the new values An error dialog box will be displayed if a modification is unacceptable Select the Revert button to revert the entries to the previous values As will be seen later the Edit window can contain multiple Edit panels To update all the Edit panels select the Accept All button to revert all the panels select the Revert All button The figure below shows the Nose Body component after the Nose Type radio button has been changed to Ogive and the Nose Droop text field has been set to 0 5 Aero Troll v0 2 0b File Edit View Help Components o 5 Nose Body 13 The analysis methodology for the component should be chosen before an analysis is performed To select the analysis method for a component right click on the Nose Body component node in the components tree to show the component popup menu and then select the desired analysis method under the Analysis Type submenu PANAIR is chosen in this case Aero Troll v0 2 0b File Edit View Help Components Rename Hide Analysis Type gt Modified Newtonian P inf Results 2 Modified Newtonian P
8. Edit View Help Components coordinate System Group C Nose Body C Fin Set Coordinate System ordinate System dordinate System 55 The above steps are repeated for the last two remaining Coordinate System components The Aero Troll window now appears as in the following figure File Edit View Help Components e coordinate System Group Nose Body C Fin Set ordinate System Group c Nose Body C Fin Set ordinate System Group c Nose Body C Fin Set ordinate System Group c Nose Body C Fin Set 2 0 D 2 0 me o Co C3 L Co C3 o Co C3 o E 56 Since the coordinate systems have the same position parameters the four groups overlay one another To separate the the groups the Z Shift Y Shift and Phi Rot parameters for the Coordinate System components are set so the fin tips touch and a body is at 12 o clock 3 o clock 6 o clock and 9 o clock The configuration forms a After changing the view the image appears as follows File Edit View Help f Components c Coordinate System C Group 7 Nose Body C Fin Set ordinate System Group c Nose Body C Fin Set ordinate System Group c Nose Body 3 Fin Set C Coordinate System E Group o 5 Nose Body C Fin Set U 9 e e 19 v E Co C3 e 57 Next the AT Analysis Mach parameter is set to 1 5 and the case is ex
9. Theta for the first fin to 90 0 degrees Theta for the second fin to 270 0 degrees and Theta Panels to 6 for both fins After completion the Edit panel for the Fin Set component should look like the following two figures Edit Window AT Analysis Nose Body Fin Set X Shift Y Shift Psi Rot i Tht Rot Body Wake Local Wake Fin Wake Body Radius Root Chord Tip Chord Span Is L E Sweep L E Sweep Hinge Line Chord Panels Span Panels Base Panels Fins Only Def In B C Show fin outlines Inc Base Load More Fin 1 Theta 90 0 Accept Accept All 73 Edit Window AT Analysis Nose Body Fin Set Inc Base Load v More Fin 1 Theta Include Fin Dihedral Deflection Include Body Theta Panels 6 Delete Fin 1 Fin 2 Theta Include Fin Dihedral Deflection Include Body v Theta Panels Delete Fin 2 Add Fin Accept All Just as with the Nose Body component it is important that the body wake is not included and that the base is removed by setting the Base Panels to zero since the Body component to be created next will supply t
10. and 4 the TE check box for the tank body this will display the outboard edge abutment After the selections are made the PANAIR check edit panel will look like the figure below 26 Edit Window PANAIR AT Analysis Check PANAIR Auto Check y Show PANAIR geometry Show Invalidated PANAIR geometry Edge Visibility ORed ANDed Network Show All Hide All Boundary Show All Hide All Top Edge Show All Hide All Bot Edge Show All Hide All Edge 1 Show All Hide All Edge 2 Show All Hide All Edge 3 Show All Hide All Edge 4 Show All Hide All Net Bndr TE BE Edg1 Edg2 Edg3 Edg4 Name v v v v v Wing swing i1 Eai v vj Wing pwing0i1 v iv Wing wake 1w0 v 7 Wing wake1w1 v Nose Body nosebdi2 v Nose Body body0i2 Y Nose Body base0i2 v 7 Nose Body nose2w0 SIRI SIRI IS ISI IST IS Accept Accept All Revert All An added degree of control for the abutment visibility is provided by the Edg columns One Edg column exists for each of the four edges The selection of an Edg check box specifies if the abutment for that edge will be shown or not In general the best way to learn how to use the PANAIR check tool is to play with it Now to give another example of the PANAIR check too
11. as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system 52 Group The Group component has the same feature set as the Coordinate System component In addition the Group component provides a container for which all the integrated loads and moments of the attached components will be combined The combined loads will be non dimensionalized by the Group component reference areas and lengths The Group component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system Z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same
12. included in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Front Chord The chord length of the forward portion of the wedge The value must be greater than zero Middle Chord The chord length of the middle portion of the wedge The value must be greater than or equal to zero Back Chord The chord length of the back portion of the wedge The value must be greater than or equal to zero Span The span of the wedge The value must be greater than zero Front Droop The droop of the front of the wedge Measured parallel to the local z axis Back Droop The droop of the nose Measured parallel to the local z axis Half Thickness The half thickness of the middle portion of the wedge The value must be greater than zero Trailing Half Thickness The half thickness of the base The value must be greater than or equal to zero Front Panels The number of panels on the front portion of the wedge The value must be greater than zero Middle Panels The number of panels on the middle portion of the wedge The value must be greater than zero 45 Back Panels The number of panels on the back portion of the wedge The value must be greater than zero Span Panels The number of panels on the span of the wedge The value must be greater than zero Thickness Panels The number of
13. moment values will be rotated to take into account the deflection If selected 37 the fin paneling will appear to be undeflected in the Main Display panel However the fin outline if it is activated will be deflected to provide visual feedback to the user In general when using the PANAIR analysis method this check box should be selected for cases with deflection Show fin outlines If selected the fin outline will be shown If the Def In B C checkbox is not selected then fin outline and the fin panels will coincide However if the Def In B C checkbox is selected then fin outline will represent the fin as it would appear if it were physically deflected while the fin panels represent a physically undeflected fin Inc Base Load If selected the base will not be used in the calculation of the aerodynamic loads More Display the advanced settings dialog The following input parameters are for a fin Note that the deflection angle is applied first then the dihedral angle is applied This is to insure that the root chord does not pierce the body Theta The theta location of the fin hinge line A theta value of zero represents the top of the body The theta value is positive in a clockwise direction when viewed from the back towards the front The value is in degrees Include Fin If unselected this section will not include a fin Dihedral The dihedral of the fin A positive value is in a counter clockwise direction when vie
14. panel for the Nose Body component The Nose Body component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler 32 angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Include Wake If selected
15. panels on the half thickness The value must be greater than zero Wedge Tips Selection of a checkbox indicates whether a wedge tip should be paneled If the Starboard checkbox is selected then the starboard wedge tip will be paneled If the Port checkbox is selected then the port wedge tip will be selected Inc Base Load If selected the base will not be used in the calculation of the aerodynamic loads More Display the advanced settings dialog Box The Box component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the sam
16. requested Show PANAIR geometry If selected the PANAIR check geometry will be shown If the overall geometry is modified then the PANAIR check geometry will become invalidated and if the Show Invalidated PANAIR geometry is unselected will be hidden Show Invalidated PANAIR geometry If selected the PANAIR check geometry will continue to be shown even after it is invalidated This check box is disabled if the current check geometry is valid Edge Visibility Modifies the conditions for when an abutment is shown If the ORed radio button is selected then the abutment will be shown if either of the TE or BE check boxes for the networks which form an abutment is selected If the ANDed radio button is selected then the abutment will be shown if both of the TE or BE check boxes for the networks which form an abutment are selected Network Show Hide All Show or hide all the networks Selecting the buttons is identical to selecting or unselecting all the Net check boxes Boundary Show Hide All Show or hide all the boundaries Selecting the buttons is identical to selecting or unselecting all the Bndr check boxes Top Edge Show Hide All Show or hide all the top edges Selecting the buttons is identical to selecting or unselecting all the TE check boxes Bot Edge Show Hide All Show or hide all the bottom edges Selecting the buttons is identical to selecting or unselecting all the BE check boxes Edge 1 Show Hide All Show or hide all
17. the geometry components are hidden the Aero Troll window will look like the image below 20 Aero Troll v0 2 0b File Edit View Help Components o 5 Nose Body The various networks are shown in blue with a black or blue border in the figure above In this case there are four networks nose body base and wake The surface networks nose body and base have a black border and the surface is colored in with blue The wake networks have a blue border and the wireframe of the wake network is colored blue The edge of the network is colored according to the type of abutment A green abutment indicates that the side of an edge has successfully connected to another edge A yellow abutment indicates that the side of an edge has either connected to the other side of that edge or that the side belongs to a trailing edge of a wake which extends to infinity A clear abutment indicates that the edge coalesces to a single point A red abutment indicates that either the edge has connected to an incompatible edge or that it has not connected at all It is up to the end user to ensure that the abutments are connected as expected The figure below shows the PANAIR check view of a tank attached to a wing tip 21 Aero Troll v0 2 0b TOR File Edit View Help Components Y o C Wing o CI Nose Body In the case shown above there are eight networks 1 starboard wing 2 port wing 3 starboard wing wake 4 port wing
18. the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system Z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system 36 Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Body Wake If selected wake panels for the body will be included in the PANAIR calculation Local Wake f selected the wake will follow along the x axis of the parent coordinate system otherwise
19. this check box is selected then at least one of the box faces should be disabled to open the box up Flow Through Front Face If selected the front face will be created as a flow through face A flow through face always has an inner and outer side so the Two Sided check box must be unselected for Flow Through Front Face to be selected Inc Base Load If selected the base will not be used in the calculation of the aerodynamic loads More Display the advanced settings dialog 47 Panel The Panel component serves as a general surface component Currently the user can specify two types of surfaces The first is a quadrilateral and the second is user defined For the quadrilateral the x y and z coordinates for the four vertices are specified by the user and panel corner points are determined by bilinear interpolation For the user defined option the user specifies a python function in a script file and the panel corner points are determined by executing that function once for each panel point The name of the function is expected to be ssToPt Aero Troll uses jython for interpreting the python file An example of a Panel component python script file is shown below beginning of file an example panel python script file ssx chord ratio 0 lt ssx lt 1 0 ssy span ratio 0 lt ssy lt 1 0 pp a three element array to return point coordinates pp 0 x pp 1 Y pp 2 z ef ssToPt ssx ssy pp width 2 0 len
20. to form the wing The total number of panels along the span of the wing is the sum of the number of span panels along each region Each region will be represented by a panel network for a PANAIR analysis Tip Chord The tip chord of the region The value must be greater than or equal to zero Span The span of the region The value must be greater than zero L E T E Sweep The leading or tailing edge sweep of the wing specified in degrees Whether it is a leading or trailing edge value depends on the state of the Is L E Sweep check box The sweep must be between 90 and 90 degrees Is L E Sweep If selected then the sweep is the leading edge sweep Otherwise the sweep is the trailing edge sweep 42 Dihedral The dihedral of the wing region specified in degrees Twist The twist of the wing region tip specified in degrees The wing tip is rotated about the twist point located on the wing region tip which is specified by the Twist Loc parameter Twist Loc Specified the twist point The twist point of a wing region is located on the wing region tip chord and is a fraction of the tip chord rearward from the tip chord leading edge A value of 0 0 indicates that the twist point is located at the wing region tip chord leading edge and a value of 1 0 indicates that the twist point is located at the wing region tip chord trailing edge Span Panels The number of panels along the span The value must be greater than zero Copy Flap Ra
21. wake 5 tank nose 6 tank body 7 tank base and 8 tank wake All the abutments are correctly connected in this case The top and bottom sides of the leading edge of a wing connect yellow The top and bottom sides of the outboard tip edges of the port wing and wake connect yellow The trailing edge of the wing connects to the leading edge of the wing wake green The inboard edges of the port wing and wake connect to the inboard edges of the starboard wing and wake green The outboard edge of the starboard wing and wake connect to the tank body and wake green The tank nose coalesces to a point blank The tank nose connects to the tank body green The top outer side of the trailing tank body edge connects to the top outer side of the leading edge of the tank wake green The bottom inner side of the trailing tank body edge connects to the bottom inner side of the tank base green The top outer side of the tank base connects to the bottom inner side of the tank wake green Seeing some of this information from the PANAIR check display can be difficult so the PANAIR check edit panel allows the user to show and hide networks boundaries and abutments To open the PANAIR check edit panel right click on the AT Analysis node and select the Edit PANAIR menu item The PANAIR check edit panel is shown below 22 Edit Window PANAIR AT Analysis Check PANAIR l Auto Check J lSJ
22. 1 This LICENSE AGREEMENT is between the Python Software Foundation PSF and the Individual or Organization Licensee accessing and otherwise using this software Jython in source or binary form and its associated documentation 2 Subject to the terms and conditions of this License Agreement PSF hereby grants Licensee a nonexclusive royalty free world wide license to reproduce analyze test perform and or display publicly prepare derivative works distribute and otherwise use Jython alone or in any derivative version provided however that PSF s License Agreement and PSF s notice of copyright i e Copyright c 2007 Python Software Foundation All Rights Reserved are retained in Jython alone or in any derivative version prepared by Licensee 3 In the event Licensee prepares a derivative work that is based on or incorporates Jython or any part thereof and wants to make the derivative work available to others as provided herein then Licensee hereby agrees to include in any such work a brief summary of the changes made to Jython 4 PSF is making Jython available to Licensee on an AS IS basis PSF MAKES NO REPRESENTATIONS OR WARRANTIES EXPRESS OR IMPLIED BY WAY OF EXAMPLE BUT NOT LIMITATION PSF MAKES NO AND DISCLAIMS ANY REPRESENTATION OR WARRANTY OF MERCHANTABILITY OR FITNESS FOR ANY PARTICULAR PURPOSE OR THAT THE USE OF JYTHON WILL NOT INFRINGE ANY THIRD PARTY RIGHTS 5 PSF SHALL NOT BE LIABLE TO LICENSEE OR ANY OTH
23. AIR The installation of PANAIR depends on the OS under which Aero Troll is running Windows XP The PC version of PANAIR must be placed in the AeroTroll_v020b AT_Data PC at_panair directory and called panair exe i e the path to PANAIR from the AeroTroll v020b directory would be AT_Data PC at_panair panair exe Linux 32 bit The Linux 32 bit version of PANAIR must be placed in the AeroTroll v020b AT Data LINUX at panair directory and called Panair i e the path to PANAIR from the AeroTroll v020b directory would be AT Data LINUX at panair Panair NOTE the version of PANAIR from my copy of version 14 0 of Public Domain Computer Programs for the Aeronautical Engineer was not statically linked to the gfortran library Therefore to use this version of PANAIR either PANAIR must be recompiled statically see instructions above in the Patching PANAIR section or the LD LIBRARY PATH environment variable in the AeroTroll lin run script must be appended with the directory containing the gfortran libraries Linux 64 bit If you did not compile PANAIR under the 64 bit OS you will need to use the Linux 32 bit version of PANAIR from the Public Domain Aeronautical Software CD PANAIR must be placed in the AeroTroll v020b AT Data LINUX64 at panair directory and called Panair i e the path to PANAIR from the AeroTroll v020b directory would be AT Data LINUX64 at panair Panair Mac Note this has only been test under an Intel version The Mac version of PANA
24. AR AT Analysis Nose Body Include Wake Local Wake O Nose Type Cone Ogive Nose Radius Nose Length Body Length Tip Radius Nose Droop Tip Panels Nose Panels Body Panels Base Panels Inc Base Load Seg 1 Theta 180 0 Include Body Theta Panels 12 Delete Segment 1 Add Segment Accept Accept All Revert Revert All It is important that the wake is not included and that the base is removed by setting the Base Panels to zero since the Body component to be created later will supply the wake and base for the body 71 Next select the Accept button and the Aero Troll window should like the following figure Aero Troll v0 2 0b File Edit View Help Components o 5 Nose Body Next create a Fin Set component by right clicking on the AT Analysis component node and selecting Fin Set from the Add submenu of the AT Analysis component popup menu Once the Fin Set is created right click on the Fin Set component node to display the component popup menu and select the Edit menu item In the Fin Set edit panel set the following parameters to the values given below X Shift 23 4 Body Wake Unselected Body Radius 18 Root Chord 6 0 Tip Chord 3 0 Span 3 0 LE Sweep 45 0 Hinge Line 0 6 Base Panels 0 Def In B C Selected 72 Next delete fins 3 and 4 by selecting the Delete Fin button for those fins Then set
25. Aero Troll User s Manual v0 2 0b by Martin C Hegedus September 6 2009 INTRODUCTION Intent Aero Troll is a preliminary aerodynamic analysis tool with a graphical user interface The goal of Aero Troll is to allow a user to describe and carry out aerodynamic analysis on simplified geometries The tool supports education academic aerodynamic analysis and verification and validation efforts The software was created to broaden my knowledge of software development and aerodynamic modeling It is hoped that the tool will be helpful to others Currently the code interfaces with PANAIR A502 and includes hypersonic impact methods Work is underway to include additional methods Aero Troll is available for Linux 32 and 64 bit Windows XP and Mac Intel Aero Troll was developed and extensively tested under Linux and Windows XP Aero Troll was ported over to the Mac using a friend s machine The Mac version of Aero Troll has had very limited testing Aero Troll has not been tested under Vista Aero Troll requires the publicly available PANAIR A502 code which can be obtained from Public Domain Aeronautical Software www pdas com Aero Troll also requires the publicly available JOGL and Jython java libraries The JOGL and Jython libraries are included in the Aero Troll distribution Aero Troll requires Java 1 5 or later What s New Listed below are the additions and modifications for the new release v0 2 0b since the previous re
26. ER USERS OF JYTHON FOR ANY INCIDENTAL SPECIAL OR CONSEQUENTIAL DAMAGES OR LOSS AS A RESULT OF MODIFYING DISTRIBUTING OR OTHERWISE USING JYTHON OR ANY DERIVATIVE THEREOF EVEN IF ADVISED OF THE POSSIBILITY THEREOF 6 This License Agreement will automatically terminate upon a material breach of its terms and conditions 7 Nothing in this License Agreement shall be deemed to create any relationship of agency partnership or joint venture between PSF and Licensee This License Agreement does not grant permission to use PSF trademarks or trade name in a trademark sense to endorse or promote products or services of Licensee or any third party 8 By copying installing or otherwise using Jython Licensee agrees to be bound by the terms and conditions of this License Agreement INSTALLATION Two compressed archives exist One of the archives AeroTroll v020b tgz is tarred and gzipped The other archive AeroTroll v020b zip is zipped Please uncompress the one appropriate for you Once Aero Troll is uncompressed you will need to modify a run script inside the AeroTroll v020b directory Depending on your operating system Windows Linux or Mac open with a text editor the AeroTroll win bat AeroTroll lin or AeroTroll lin64 for a 64 bit Linux box or AeroTroll mac script located in the AeroTroll directory Then modify the AeroTroll path and java path variables located in the script to correspond to your system setup After Aero Troll h
27. IR must be placed in the AeroTroll v020b AT Data MAC at panair directory and called Panair i e the path to PANAIR from the AeroTroll v020b directory would be AT_Data MAC at_panair Panair BASIC USAGE Startup To start Aero Troll under Windows XP double click on the AeroTroll win run script Under Linux execute the AeroTroll lin script or the AeroTroll lin64 script for a 64 bit Linux box at the command line Under Mac open a terminal window and execute the AeroTroll mac script at the command line The license will be shown Please read it and if you accept the terms and conditions select the Accept checkbox and click the OK button Once accepted the license window will not be displayed at startup anymore If you would like to view the license terms and conditions at a subsequent time please select the About menu item under the Help menu Once started the Aero Troll window will be displayed This window is shown below Aero Troll v0 2 0b TOX File Edit View Help Components At the top of the window is the main menu bar Below and to the left of the main menu bar is the Components panel The Components panel is the area where geometry components will be shown as nodes in a hierarchical tree The hierarchical tree will be referred to as the component tree To the right of the Components panel is the main display panel The width of the Components panel and main display panel can be adjusted by selecting th
28. L L Ll 5 C Show PANAIR geometry Show Invalidated PANAIR geometry Edge Visibility ORed ANDed Network Show All Hide All Boundary Show All Hide All Top Edge Show All Hide All Bot Edge Show All Hide All Edge 1 Show All Hide All Edge 2 Show All Hide All Edge 3 Show All Hide All Edge 4 Show All Hide All Net Bndr TE BE Edg1 Edg2 Edg3 Edg4 Name v lv v v Wing swingOi1 Eai v C Wing pwing0i1 v Wing wake1w0 v Wing wake1w1 v Nose Body noseDi2 7 Nose Body body0i2 C v Nose Body baseDi2 Nose Body nose2w0 amp S IST IST ST S S S ISTIS ISTIST ST S S Accept Accept All Revert All The primary area of the PANAIR edit panel for modifying the visibility of the networks and abutments is the table of check buttons located at the bottom of the window The Net column controls the visibility of the networks and the Bndr column controls the visibility of the network boundary The TE and BE columns determine whether the top and bottom side of an abutment will be displayed The behavior of these columns is affected by the selection of the Edge Visibility radio buttons If the ORed radio button is selected then the abutment will be shown if one of the TE or BE check boxes for the two networks comprising the abutm
29. The reference area used to non dimensionalize the aerodynamic forces and moments The value must be greater than zero IRef The reference length used to non dimensionalize the longitudinal aerodynamic moments The value must be greater than zero bRef The reference length used to non dimensionalize the lateral aerodynamic moments The value must be greater than or equal to zero If the value is equal to zero then IRef will substitute for bRef xMom The x value for the moment center measured in the local coordinate system Positive is rearward yMom The y value for the moment center measured in the local coordinate system Positive is starboard zMom The z value for the moment center measured in the local coordinate system Positive is up Check PANAIR Execute PANAIR check Edit PANAIR Open PANAIR check edit panel Invalidate Invalidate the current solution Execute Execute a solution Results Show the results window PANAIR Helper Agent The general usage for the PANAIR helper agent was described above 30 The PANAIR component has the following parameters Check PANAIR Selection of this button will initiate a check of the PANAIR networks and abutments The action is identical to selecting the Check PANAIR menu item under the AT Analysis popup menu Auto Check If selected the PANAIR network abutments will be checked automatically before PANAIR is executed If unselected a check will occur only when explicitly
30. are then connected side edge to side edge to loop over the circumference of the body The total number of panels along the circumference of the body is the sum of the number of panels 35 in each segment Each segment will be represented by a panel network for a PANAIR analysis Theta The ending circumferential theta location for the segment The segment will start at the ending theta of the previous segment For the first segment the starting theta is the ending theta of the last segment The ending theta location must not match the ending theta location of any other segment A theta value of zero represents the top of the body The theta value is positive in a clockwise direction when viewed from the back towards the front The value is in degrees Include Body If unselected panels will not be laid out along the circumference Theta Panels The number of panels in the theta direction for this segment The value must be greater than zero Fin Set The Fin Set component is used to model fin sets Each fin in the fin set has the same planform shape The fin planforms are modeled with straight leading edge and trailing edges and the root chord and tip chord are parallel It is possible to deflect the entire fin set but currently tailing edge flaps leading edge flaps and ailerons can not be specified The Fin Set component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from
31. as been installed PANAIR must be installed in the correct location of the Aero Troll Data directory and named correctly Currently the only distributor for PANAIR that I know of is Public Domain Aeronautical Software www pdas com If you would like to model a ground plane with PANAIR you will need to obtain version 14 0 January 2009 of the Public Domain Computer Programs for the Aeronautical Engineer CD from Public Domain Aeronautical Software and patch it with the panair v14 gp patch file This patch can be downloaded from the software page at www hegedusaero com Patching PANAIR If you intend to patch PANAIR this must be done before installing PANAIR To patch PANAIR first create a folder somewhere on your hard drive give it any name and copy the SOURCE14 zip file from the PANAIR directory of the Public Domain Computer Programs for the Aeronautical Engineer CD Then unzip the file Next download the panair v14 gp patch file from the software page of www hegedusaero com into your PANAIR source directory To patch PANAIR the patch program must be installed on your machine The remaining patch instructions will depend on your OS Windows XP It is probable that you will need to download and install the patch program I downloaded mine from http gnuwin32 sourceforge net packages patch htm Next open a Command Prompt tool and cd into the PANAIR source directory Then type the following command at the command prompt you may ne
32. e divider which separates the two panels and moving the divider left or right Main Menu Bar To save an Aero Troll session select the Save As or Save menu item under the File menu The Aero Troll session file will be saved as an ASCII XML file To open a session file select the Open menu item under the File menu If a model already exists in Aero Troll the newly opened model will be appended to the existing model To quit Aero Troll select the Quit menu item under the File menu After the Quit menu item is selected a dialog box will appear which asks for confirmation of the action If the action is confirmed Aero Troll will quit immediately It is up to the user to save any work before Aero Troll is exited Quitting Aero Troll will not automatically save the current session Currently Aero Troll does not have the capability to print out a model Next to the File menu is the Edit menu The Edit menu allows the user to cut and copy components by selecting a component in the component tree and then selecting the Cut or Copy menu item To paste a component select the node in the component tree under which the component will be pasted and select the Paste menu item If the component to be pasted 1s not allowed under the selected node the Paste menu item will disabled The Edit menu also allows the user to unselect the auto close check box in all PANAIR execution windows The View menu will be described in a later section To view
33. e of a wake from the component associated with the checkbox touches a network edge of another component then Aero Troll will attach the wake to that network edge and the wake will follow along the length of that network edge If the Sticky Wakes check box is not selected then the wake will not attach to the network edge 28 Reject Wake Attachments If the Reject Wake Attachments checkbox is selected then the inboard or outboard edge of a wake from another component will not attach to a network edge of this component AT Analysis The AT Analysis base component is an analysis container class for geometry components As an analysis class it allows for the organization and execution of the geometry component analysis methods The AT Analysis base component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the global coordinate system The value is measured along the x axis of the global coordinate system Y Shift The amount that this component s coordinate system is shifted starboard from the global coordinate system The value is measured along the y axis of the global coordinate system Z Shift The amount that this component s coordinate system is shifted upward from the global coordinate system The value is measured along the z axis of the global coordinate system Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation
34. e of the prior section and select the Check PANAIR menu item Aero Troll v0 2 0b File Edit View Help Components Cut Copy Paste Delete Edit Rename Hide Hide All Show All Invalidate Execute Check PANAIR Edit PANAIR s Show PANAIR Results Aero Troll will do a rudimentary automatic check and will present a message dialog for any errors encountered To perform a manual investigation of the PANAIR networks and abutments first the PANAIR networks and abutments must be displayed and the geometry components hidden To show the PANAIR networks and abutments right click on the AT Analysis component and select the Show PANAIR menu item in the component popup menu as seen below 18 OX File Edit View Help Components o c Deactivate Cut Copy Paste Delete Edit Rename Hide Hide All Show All Add Invalidate Execute Check PANAIR Edit PANAIR Show PANAIR Results Since the PANAIR networks and abutments overlay the geometry components the geometry components need to be hidden To hide the geometry components right click on the AT Analysis component and select the Hide All menu item in the component popup menu 19 File Edit View Help Components 4 Deactivate Cut Copy Paste Delete Edit Rename Hide Hide All Show All N Add Invalidate Execute Check PANAIR Edit PANAIR Hide PANAIR Results Once
35. e order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system 46 Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Include Wake If selected wake panels will be included in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Width The width of the box The width must be greater than zero Height The height of the box The height must be greater than zero Length The length of the box The length must be greater than zero Width Panels The number of panels along the width The width panels must be greater than zero Height Panels The number of panels along the height The height panels must be greater than zero Length Panels The number of panels along the length The length panels must be greater than zero Include Face A set of check boxes to specify if a face is active or not Two Sided If selected both sides of a box face are treated as external If unselected the outer side of each box face will be treated as external and the inner side will be treated as if it was pointing inside the body If
36. ecuted The resulting image is shown below Aero Troll v0 2 0b TOK File Edit View Help Components pip inf E Coordinate System C Group o C Nose Body o 5 Fin Set c Coordinate System C Group gt 5 Nose Boay o 5 Fin Set C Coordinate System EA Group gt 5 Vose Body o 3 Fin Set c Coordinate System C Group gt 5 Nose Boay o CJ Fin Set 58 If the a geometry parameter of the original Nose Body or Fin Set is modified then all the geometries are modified For example in the figure below the first Fin Set tip chord has been changed to 1 0 Aero Troll v0 2 0b File Edit View Help Components _ C Coordinate System 4 Group gt 5 Nose Body CY Fin Set Coordinate System Group CI Nose Body o E Fin Set C Coordinate System E Group gt L7 Nose Body o 7 Fin Set C Coordinate System E Group 7 Nose Body o 7 Fin Set ANALYSIS METHODS Currently Aero Troll has the capability to execute two classes of analysis methods 1 PANAIR and 2 Local Surface Methods In both cases the description given will be very brief The reader is STRONGLY encouraged to read the references relating to these two methodologies PANAIR PANAIR is an external program and must be obtained from www pdas com The reader is encouraged to read the documentation which comes with PANAIR Local Surface Methods Included with A
37. ed to modify the command to reflect your patch program installation gt C Program Files GnuWin32 bin patch binary lt panair vl4 gp patch Note don t close the command prompt since you will need it to compile PANAIR For compiling I used gfortran I downloaded the mingw build of gfortran from http gcc gnu org wiki GFortranBinaries To compile PANAIR type the following command at the command prompt gt gfortran f90 O o panair static libgfortran This completes the patch and compilation of PANAIR under Windows XP Linux For me the patch program was included in my Linux distribution But if you need to you can download it from ftp ftp gnu org gnu patch To patch PANAIR open a command prompt window and cd into the PANAIR source directory Then type the following command at the command prompt you may need to modify the command to reflect your patch program installation gt patch binary lt panair v14 gp patch Note don t close the command prompt since you will need it to compile PANAIR For compiling I used gfortran To compile PANAIR type the following command at the command prompt gt gfortran f90 O o Panair static libgfortran This completes the patch and compilation of PANAIR under Linux Mac Unfortunately I don t own a Mac so I m unable to give explicit instructions on how to patch and compile PANAIR under the Mac OS However I guess it would be similar to the Linux method Installing PAN
38. eld points plane Length The length of the field points plane Width Points The number of points along the width of the field points plane Length Points The number of points along the length of the field points plane 51 Coordinate System The Coordinate System component provides the means to introduce a coordinate system within the model Any component added to this component will inherit the coordinate system of this component The Coordinate System component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order
39. ent are selected If the ANDed radio button is selected then the abutment will be shown if both of the TE or BE check boxes for the two networks comprising the abutment are selected For example the figure below shows the PANAIR check view when the ORed radio button is selected and all the TE and BE check boxes are unselected 23 TOX Z Aero Troll v0 2 0b File Edit View Help Components o 7 Wing o C Nose Body WO eis Next the following view shows the PANAIR check view after the BE checkbox for the starboard wing is selected 24 TOX Aero Troll v0 2 0b File Edit View Help Components o 7 Wing 5 Nose Body After the ANDed radio box is selected the PANAIR check view will look like the following image 23 Z Aero Troll v0 2 0b TOX File Edit View Help i Components o 7 Wing o 5 Nose Body As can be seen by the figure above none of the starboard wing abutments are shown This is because the TE or BE check boxes for the networks which abut to the starboard wing network are not selected To show the top edge abutments for the starboard wind the following check boxes must be selected 1 the TE check box for the starboard wing this will display the leading edge abutment 2 the BE check box for the port wing this will display the inboard edge abutment 3 the BE check box for the starboard wake this will display the trailing edge abutment
40. er of points mm len xx find the bracketing values for ii in range 1 mm if xin gt xx ii 1 and xin lt xx ii or xin lt xx ii 1 and xin gt xx iil break if ii mm raise Exception CubicSplineYY Bracketing values could not be found return value dx xx ii xx ii 1 dx1 xx ii xin dx2 xin xx ii 1 return dd ii 1 dx1 dx1 dx1 dd ii dx2 dx2 dx2 6 0 dx yy ii 1 dx dd ii 1 dx 6 0 dx1 yy ii dx dd ii dx 6 0 dx2 end of cubic spline evaluation method Cublic Spline Derivative method Based on spline method from Numerical Methods for Engineers Second Edition d Steven C Chapra Raymond P Canale ef CubicSplineDY xin xx yy dd get number of points mm len xx find the bracketing values for ii in range 1 mm if xin gt xx ii 1 and xin lt xx ii or xin lt xx ii 1 and xin gt xx iil break if ii m raise Exception CubicSplineYY Bracketing values could not be found return value dx xx ii xx ii 1 dx1 xx ii xin dx2 xin xx ii 1 return 3 0 dd ii 1 dx1 dx1 dd ii dx2 dx2 6 0 dx yy ii 1 dx dd ii 1 dx 6 0 A yy ii dx dd ii dx 6 0 end of cubic spline derivative method beginning of bodySSToPts method def bodySSToPt ssx ssy pp if ssx 1 0 pp 0 33 3333 radius 1 6666 2 0 else pp 0 ssx 100 3 radiu
41. ero Troll are a set of supersonic hypersonic windward and leeward local surface methods The selection set of windward methods are 1 modified Newtonian 2 tangent wedge and 3 tangent cone The selection set of leeward methods are 1 ps and 2 Prandtl Meyer expansion The impact methods are based on those described in the 59 Program Formulation volume of the Mark 1V Supersonic Hypersonic Arbitrary Body Computer Program documents http handle dtic mil 100 2 AD778444 The user is encouraged to review the sections pertaining to the above method local surface methods within the program formulation volume The current local surface methods in Aero Troll do not take into account shielding DISCUSION PANAIR Below are several topics regarding PANAIR and Aero Troll Paneling for PANIR The setup of a proper input deck for PANAIR can be complex Some of the issues to insure are 1 Control points are not overly influenced by panels other than the panel the control point belongs to 2 Network edges are abutted correctly to maintain continuity of doublet and source strengths 3 Wakes are set up correctly to adequately model the physical wake and to ensure gaps between wake sheets do not exist Listed below are a couple of helpful remarks regarding usage The example geometry used in the remarks comes from the NASA TM 2001 210652 Body Fin 11 example which is described later 1 Panels should match up An example of this is the need to match up the
42. espect to the parent coordinate system Include Wake If selected wake panels will be included in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Body Type A radio button grouping for selecting whether the radius distribution between the beginning and end of this component is a Cone Forward Ogive or Backward Ogive Forward Radius The radius at the beginning of the body The value must be greater than zero Aft Radius The radius at the end of the body The value must be greater than zero Body Length The length of the body Measured parallel to the local x axis The value must be greater than or equal to zero Body Droop The amount by which the end of the body is higher than the beginning of the body Body Panels The number of panels laid out along the axis of the body The value must be greater than zero Base Panels The number of panels on the base along the radius The value must be greater than or equal to zero If the value is zero then a base will not be included Inc Base Load If selected the base will not be used in the calculation of the aerodynamic loads More Display the advanced settings dialog The following input parameters are for a body segment Each body segment represents a set of panels laid out along a portion of the circumference The segments
43. et the MidBody Bot component parameters as follows Phi Rot 180 0 The next set of panel components will be used to define the aftbody The methodology is similar to that of building the forebody and midbody Create a Panel component and name it AftBody Top Next set the component s parameters as follows Categroy User Defined Function File examples NACA RM L50H08ScriptsNACA RM L50H08 aft body py Two Sided unselected Chord Panels 10 Span Panels 6 To create the aftbody bottom panel copy the AftBody Top component and paste it under the AT Analysis component Next rename the new AftBody Top component to AftBody Bot Next set the AftBody Bot component parameters as follows Phi Rot 180 0 85 The current wing component for Aero Troll requires that the root and tip chord be straight Since the wings in this example have curved root chords panel components will be used to describe the wings in this example Create a Panel component and name it Star Wing Next set the component s parameters as follows Include Wake Two Sided Categroy User Defined Function File examples NACA RM _L50HO08 Scripts NACA RM L50H08 wing py Chord Panels 5 Span Panels 10 To create the port side wing panel copy the Star Wing component and paste it under the AT Analysis component Next rename the new Star Wing component to Port Wing Next set the Port Wing component parameters as follows Phi Rot 180 0 The next co
44. forward or backward to rotate the image about the x axis of the screen Moving the mouse right or left will rotate the image about the y axis of the screen To zoom the image hold down the middle mouse button and move the mouse forward to zoom out of the image or move the mouse backward to zoom into the image The view for the Main Display panel can be reset to one of six predefined views top bottom right left front and back by selecting the view from the View menu located in the main menu bar 17 Checking PANAIR Abutments An important step in the creation of a PANAIR solution is the inspection of the network edge abutments Each network has four edges and each edge has a top and bottom side Each side of the four edges of a panel network must do one of the following 1 connect to an edge side of this or another network 2 connect to the opposite side of this edge or 3 coalesce into a single point In addition each side of an edge is either an internal or external type depending on whether it is on the inside or outside of the geometry An edge side can only connect to another side of the same type So an internal side must connect to an internal side and an external side must connect to an external side If an edge side incorrectly connects to another edge side or remains unconnected then the solution from PANAIR will be erroneous To check the PANAIR network abutments right click on the AT Analysis component node in the exampl
45. gth 3 0 pp 0 ssx length pp 1 ssy width ppI 2 1 0 end of file Q e Hb e ouk dock ob HHH The script above will produce a rectangle 2 wide and 3 long Three parameters are passed to the ssToPt routine The first two ssx and ssy are the ratios along the chord and span for the panel corner points The values will range between 0 0 and 1 0 inclusively The last parameter pp is a three element array which must be set inside the function to the coordinates of the point specified by ssx and ssy The first element of the array pp 0 is the x value The second element of the array pp 1 is the y value And the third element of the array pp 2 is the z value A more complex exampling involving Panel components is given below in the NACA RM L50HO08 example section The Panel component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis 48 T Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system Z axis Psi Rot The amount in degrees that this component s coordinate syste
46. hat scaling the geometry may change the number of significant figures in the input file and thus affect the results a little Determination of pressure Pressures are determined by Aero Troll using the compressible Bernoulli equation with velocities calculated by PANAIR Determination of loads The loads are determined by integrating p p over the body EXAMPLES NASA TM 2001 210652 Body Fin 11 The following example describes the construction of a simple Fin Body configuration given in NASA TM 2001 210653 A PDF version of the TM can be downloaded from the NASA technical report server ntrs nasa gov For this example the diameter of the body is 3 0 the nose length is 9 0 and the overall length is 36 0 The body has an ogive nose There are two fins one on the starboard and one on the port side The fin span is 3 0 the root chord is 6 0 the tip chord is 3 0 and the leading edge sweep is 45 0 degrees The hinge line is located at 6096 of the root chord and connects with the body at 27 0 rearward from the nose tip The reference area is equal to the base area the reference length is equal to the diameter and the moment center is located at an x location of 21 0 Four components will be created 1 an AT Analysis Component 2 a Nose Body component 3 a Fin Set component 4 and a Body component The xml input file for this case is in the examples directory AT Analysis Component First start Aero Troll by double clicking on AeroT
47. he wake and base for the body 74 Next select the Accept button and the top and side views should look like the following two figures File Edit View Help Components gt 5 Nose Body o CY Fin Set 75 Aero Troll v0 2 0b File Edit View Help Components o 5 Nose Body o 5 Fin Set Next create a Body component by right clicking on the AT Analysis component node and selecting Body from the Add submenu of the AT Analysis component popup menu Once the Body is created right click on the Body component node to display the component popup menu and select the Edit menu item In the Body edit panel set the following parameters to the values given below X Shift 29 4 Forward Radius 1 5 Aft Radius 1 5 Body Length 6 6 Inc Base Load Unselected Next add another body segment by clicking on the Add Segment button at the bottom of the Body edit panel Then set Theta for the first body segment to 90 0 degrees Theta for the second body segment to 270 0 degrees and Theta Panels to 6 for both body segments 76 After completion the Edit panel for the Body component should look like the following figure i Edit Window OX AT Analysis Nose Body FinSet Body Include Wake r LocalWake Body Type 8 Cone Forward Ogive O Backward Ogive Forward Radius Aft Radius Body Length Body Droop Body Panels Base Panels
48. ify a rectangular grid of points at which the pressure in the field is calculated 4 Circumferential segments were added to the Nose Body component 5 Individual circumferential segments for Nose Body and Body components can be deactivated 6 Body component was modified to allow for varying radial distribution Currently either a linear or circular arc ogive distribution can be selected 7 Sweep for fins can be specified by either the leading or trailing edge 8 The ability to copy cut and paste components has been added 9 The ability to hide components has been added 10 The ability to unset auto close has been added 11 The ability to clear all the components from the component tree by selecting a menu item from the component tree popup menu has been added 12 The ability to specify whether a wake will stick to a component has been added LICENSES Aero Troll License Copyright c 2009 Martin C Hegedus All Rights Reserved Copying reproduction or publication of all or part of Aero Troll is prohibited unless expressly authorized by Martin C Hegedus This program and components are distributed in the hope that they will be useful but WITHOUT ANY WARRANTY without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE The software is offered AS IS Martin C Hegedus and anyone associated with the development and distributions of any part of Aero Troll will not be liable to any party for a
49. l all the check buttons of the PANAIR edit panel are reverted back to being selected and the wing tip tank will be moved slightly forward so that the panels between the tank body and wing tip do not align After the tank has been moved the PANAIR check must be performed again by selecting the Check PANAIR button in the PANAIR check edit panel or by selecting the Check PANAIR menu item in the AT Analysis popup menu The figure below shows the result of the new check 27 Aero Troll v0 2 0b File Edit View Help Components o 7 Wing o 5 Nose Body As can be seen from the figure above after the shift the starboard wing tip does not abut with the tank body anymore instead the starboard wing tip connects with itself This will create an erroneous result COMPONENTS This section describes each component Some of the components below allow for specification of how a wake interacts with components This is done through advanced settings The advanced settings for a component can be accessed by selecting the More button located in the edit panel for that component If a component supports these advanced settings it will be mentioned in the descriptions below The current two advanced settings are described below The Accept button in the edit panel for a component must be selected after the advanced setting for that component is changed Sticky Wakes If the Sticky Wakes check box is selected and the inboard or outboard edg
50. leading edge The Wedge component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system Z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler 44 angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Include Wake If selected wake panels will be
51. lease v0 01a 1 A PANAIR helper agent was added which displays the PANAIR abutments and performs rudimentary checks on them 2 Supersonic Hypersonic local surface methods were added The selection set of windward methods are 1 modified Newtonian 2 tangent wedge and 3 tangent cone The selection set of leeward methods are 1 po and 2 Prandtl Meyer expansion The impact methods are based on those described in the Mark IV Supersonic Hypersonic Arbitrary Body Computer Program http handle dtic mil 100 2 AD778444 The current local surface methods in Aero Troll do not take into account shielding 3 The following components were added a Wing The Wing component allows for deflected leading and trailing edges and for changes in dihedral along the span The current wing component does not model thickness or camber b Box One or more of the six Box component sides can be eliminated The forward face of the box can be specified to PANAIR as a flow through face c Panel The Panel component allows the user to specify a surface by means of a quadrilateral or a python function d Ground Plane The Ground Plane component specifies the X Y plane Z 0 as a plane of symmetry for PANAIR To correctly model a horizontal plane of symmetry the PANAIR program must be patched with a patch obtainable from www hegedusaero com Instructions for applying the patch are given below e Field Pts The Field Pts component allows the user to spec
52. ltiple trailing legs can not be accounted for Future versions of Aero Troll will be more robust in regards to handling a wake from a forward fin set to a rear one 66 Another example of a wake intersection is shown below 5 Only one fin set should be modeled with PANAIR Because of the current limitations with wakes as described in item 4 above only one fin set should be modeled Input files When Aero Troll sets up the execution of a PANAIR run it creates an input file with a random name places the input file for Windows XP in the AeroTroll_v020b AT_Data PC at_panair directory and creates a working directory for PANAIR with the same base name as the input file For Linux the file and working directory is placed in the AeroTroll_v020b AT_Data LINUX at_panair directory Once Aero Troll is finished with the working directory it is deleted Under some conditions such as if Aero Troll crashes which happens very infrequently but it does happen the input file and directory will not be deleted Therefore occasionally it is necessary to go into the at_panair directory and delete any input files and directories which exist 67 One more item to mention about PANAIR input files The input file for PANAIR is formatted therefore the input fields are of fixed width Aero Troll maximizes the number of significant figures it can place in a field by selecting either scientific notation or decimal floating point The consequence is t
53. lysis methods The following parameters are for visual purposes only and do not effect the interpretation of the flap A ground plane can only be added to an AT Analysis component As mentioned in the installation instructions in the beginning of this document the PANAIR code must be patched and recompiled for the Ground Plane component to work correctly X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Width The width of the ground plane This value is for display purposes only since the ground plane extends to infinity in global coordinate systems x y plane Length The length of the ground plane This value is for display purposes only since the ground plane extends to infinity in global coordinate systems x y plane Width Panels The number of panels along the width of the ground plane This value is for display purposes only 50 Length Panels The number of panels along the length of the ground plane This value is for display purposes only Field Pts The Field Pts component is used to query the flow field by means of a grid of points Currently the Field Pts component only has meaning for a PANAIR analysis since surface
54. m is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Include Wake If selected wake panels will be included in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Category Currently the two types which can be chosen are Quadrilateral and User Defined Each category has different input requirements which are listed below Quadrilateral For the quadrilateral category the four corners of the quadrilateral are required as input The labels for the four corner points are 1 Front Port 2 Back Port 3 Front Starboard and 4 Back Starboard The x y and z coordinate for each corner point is required User Defined The user defi
55. meter A Twist Loc value of 0 0 indicates that the twist point is located at the region tip chord leading edge and a Twist Loc value of 1 0 indicates that the twist point is located at the region tip chord trailing edge Assuming the first wing region has zero dihedral the wing region coordinate system coincides with the deflected hinge line coordinate system The parameter Dihedral of the first wing region specifies the amount the x axis of the wing region coordinate system is rolled about the x axis of the deflected hinge line coordinate system Assuming no shifts or rotations the deflected hinge line coordinate system coincides with the wing component coordinate system The wing hinge coordinate system is shifted and rotated from the wing component coordinate system by amounts specified by the Y Shift Hinge Yaw Angle Hinge Cant Angle Incidence Angle and Def Angle parameters First the incidence and deflection angle are applied to pitch the wing Then the hinge cant angle is applied to roll the wing Then the hinge yaw angle is applied to yaw the wing Finally the y shift is applied to shift the wing outward from the wing component coordinate system 39 Assuming no shifts or rotations the wing component coordinate system coincides with the parent coordinate system The parameters X Shift Y Shift Z Shift Psi Rot Tht Rot and Phi Rot specify the amount the wing component coordinate system is shifted and rotated from the parent coordi
56. methods do not affect the flow field The Field Pts component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system Z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Width The width of the fi
57. mponent which models the sting is a Body component with the following parameters X Shift 33 3333 Forward Radius 0 8333 Aft Radius 0 8333 Body Length 10 0 For this component a second segment should be added The Theta parameter for the first segment should be set to 90 degrees and the Theta parameter for the second segment should be set to 270 degrees The Theta Panels parameter for both segments should be set to 6 Setting the segment edges at 90 and 180 degrees allows the wake from the wings to attach to the body The current geometry is shown below 86 Aero Troll v0 2 0b File Edit View Help Components 5 ForBody Top 5 ForBody Bot o 5 MidBody Top o 5 MidBody Bot o 5 AftBody Top o 7 AftBody Bot o 7 Star Wing o C Port Wing This completes the geometry buildup for this example 87 APPENDIX A Script Listings for NACA RM L50H08 Example HEHEHEHE beginning of NACA RM L50H08 py script import math Tridiagonal solver NOTE order is as follows bl cl a2 b2 c2 43 bs 3 a4 b4 def TriDiag aa bb cc dd get size mm len dd set first value dd 0 dd 0 bb 0 loop through other values for ii in range 1 mm cc ii 1 Mo ae are ae 1 bb iil bb ii aa ii cc ii 1 dd ii dd iil aa ii js diii 1 bb ii back substitute for ii in range mm 1 0 1 dd ii 1 dd ii 1 cc ii 1 dd ii end of TriDiag method
58. nate system The Wing component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Body Wake If selected wake panels for the body will be i
59. ncluded in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Reflect If selected the wing will be mirrored about the x z plane of the component Well mostly If a leading or trailing edge has any roll deflection then that deflection will be opposite on the mirrored side 40 Show wing outlines If selected an outline of the true geometry of the wing will be shown in addition to the paneled geometry Y Shift The amount that the wing hinge point see Hinge Line below is shifted starboard from the wing x z plane The value is measured along the wing component coordinate system y axis The hinge point transformations are done in the following order 1 The Hinge Cant Angle 2 The Hinge Yaw Angle and 3 Y Shift The hinge point transformations do not effect the wing coordinate system Hinge Yaw Angle The amount in degrees that the wing is yawed about a line which passes through the hinge point and is parallel to the wing component coordinate system z axis Positive values rotate the wing tip forward The hinge point transformations are done in the following order 1 The Hinge Cant Angle 2 The Hinge Yaw Angle and 3 Y Shift The hinge point transformations do not effect the wing coordinate system Hinge Cant Angle The amount in degrees that the wing is canted up wing tip up ab
60. ned surface geometry requires the specification of python file which contains the ssToPt function How the path should be saved to the Aero Troll session file depends on the setting of the Path radio buttons If the Path is set as Relative then the path will be saved relative to the path of the executable This requires that the script file be located at or below the executable directory If the Path is set as Absolute then the path will be saved as an absolute path from the root directory An absolute path is system dependent whereas a relative one is not 49 Type The type of panel this component represents The three choices are 1 Surface 2 Base or 3 Wake A distinction between the Surface and Base types exists only for a PANAIR analysis For the local surface methods the Surface and Base types are treated the same A Wake type only has meaning for a PANAIR analysis A Wake type does not influence the local surface method Two Sided If selected this component is two sided in other words both sides are exterior surfaces Chord Panels The number of panels along the chord Span Panels The number of panels along the span Normal Vector Len The length of the normal vector Show NV If selected the normal vector will be shown More Display the advanced settings dialog Ground Plane The ground plane component specifies that a x y plane of symmetry should exist in the analysis The ground plane component is a flag to the ana
61. nels is set to zero and Include Wake is unselected since the body base and wake are handled by another component The next component to be created is a Fin Set component with the following parameters X Shift 5 Body Wake Unselected Root Chord 3 0 Tip Chord 0 5 Span 2 5 Base Panels 0 Next delete the fins at 0 degrees and 180 degrees and set the Theta Panels for the two remaining fins to 6 The Base Panels is set to zero and Include Wake is unselected since the body base and wake are handled by another component The geometry up to this point is shown in the figure below Aero Troll v0 2 0b File Edit View Help Components gt 5 Nose Body o c Fin Set The next component to be created which models the body segment between the wing and tail is a Body component with the following parameters 80 X Shift 8 0 Include Wake Unselected Body Length 2 5 Base Panels 0 For this component a second segment should be added The Theta parameter for the first segment should be set to 90 degrees and the Theta parameter for the second segment should be set to 270 degrees The Theta Panels parameter for both segments should be set to 6 Setting the segment edges at 90 and 180 degrees allows the wake from the wings to attach to the body The Base Panels is set to zero and Include Wake is unselected since the body base and wake are handled by another component The current geometry is shown below Aero Tr
62. ng body configuration given in NASA RM L50H08 A PDF version of the RM can be downloaded from the NASA technical report server ntrs nasa gov This example relies on the use of python scripts to define the body and wing The python scripts are somewhat involved so they will not be described in this section However the scripts are included in the appendix and the user is encouraged to look them over or to dig into the actual scripts located in the examples NACA RM L50H08 Scripts directory Currently Aero Troll does not have a graphical means of allowing the user to interactively construct arbitrary geometry segments However python scripts can be used to perform this task Hopefully a user interface for constructing arbitrary geometry segments will be available in future versions of Aero Troll 83 This geometry is made up of eight Panel components and one Body component Six of the Panel components will be used for the body and two for the wing After creating an AT Analysis component create a Panel component and name it ForBody Top Next set the component s parameters as follows Categroy User Defined Function File examples NACA RM L50H08criptsNACA RM L50H08 for body py Two Sided unselected Chord Panels 10 Span Panels 6 To create the forebody bottom panel copy the ForBody Top component and paste it under the AT Analysis component To do this right click on the ForBody Top component and select the Copy menu item Nex
63. nu This is shown in the figure below Aero Troll v0 2 0b File Edit View Help Components Geometry AT Analysis Under the Add menu the user can also create a Geometry base component The Geometry base component accepts geometry components just as the AT Analysis component does but unlike the AT Analysis component it does not associate the attached components with one or more analysis methods The Geometry base component is a convenient storage location for complex geometries comprised of multiple sub geometries Links which are described later can then be used to reference the geometries in the Geometry base component from the Analysis base components In general the majority of analysis is with an AT Analysis component only Once an AT Analysis component is created it can be populated with components To attach a component to an AT Analysis component right click on the AT Analysis component tree node to show the component popup menu and select one of the eleven geometry components from the Add menu This is shown in the figure below Aero Troll v0 2 0b File Edit View Help Components Add Nose Body Invalidate Body Is Execute Fin Set Pee Wing Wedge Box Check PANAIR Edit PANAIR Results Panel Ground Plane Field Pts Coordinate System Group The eleven components are 1 Nose Body 2 Body 3 Fin Set 4 Wing 5 Wedge
64. number of circumferential panels between a forward and aft component Shown below is a geometry with going from forward to back a Nose Body Fin Set and Body component 60 In this case each component has twelve panels on the circumference 61 If the number of panels on the circumference for the Nose Body component is changed to eleven then the panels would not align This is shown below Misaligned Panels Under some circumstances this will cause the PANAIR panel networks to butt up incorrectly 62 2 A Body component should be segmented so the segment edges match up with wakes If an edge of a wake is connected to a body then that wake must connect to a panel network edge Each Body segment as described in the Body component section is described by a unique panel network Therefore if a wake passes next to a Body component that Body component must be segmented so the wake connects to a segment edge This is shown in the image below In this case a fin and thus wake is at 90 and 270 degrees Therefore the body has two body segments One body edge has an edge at 90 degrees and the other has one at 270 degrees The fact that the wake connection to the body edge is valid is indicated by the blue wake panel grid shown in the image above 63 For the following image the first body segment was give an edge at 100 degrees instead of 90 degrees Since the wake from the starboard fin 90 degrees no longer connec
65. ny direct indirect special incidental or consequential damages arising out of any use of this software While every attempt has been made to identify and remove programming errors within the software there remains a high probability that programming errors remain in the software It is possible that some of these errors could cause results from an analysis to be incorrect In addition the analysis results may also be affected by other identified unidentified and unknown uncertainties and errors The causes of these uncertainties and errors are but are not limited to physical approximation physical modeling geometry modeling round off iterative convergence discretization and incorrect input Aero Troll and associated components are distributed WITHOUT ANY WARRANTY that usage errors assumptions uncertainties or any other aspect associated with Aero Troll its components and its analysis methods are documented or that the documentation is accessible to the end user It is the responsibility of the end user to accept all analysis answers with GREAT CAUTION and SKEPTISM JOGL License Copyright c 2003 2007 Sun Microsystems Inc All Rights Reserved Redistribution and use in source and binary forms with or without modification are permitted provided that the following conditions are met Redistribution of source code must retain the above copyright notice this list of conditions and the following disclaimer Redist
66. oll v0 2 0b File Edit View Help Components gt 5 Nose Body gt CY Fin Set o 5 Body The next component to be created which models the vertical tail is a Fin Set component with the following parameters X Shift 10 5 Root Chord 2 0 Tip Chord 1 0 Span 1 5 LE Sweep 50 0 81 For this component the Include Fin checkbox for fin 2 3 and 4 should be unselected The segment edges located at 90 and 180 degrees allows the wing wakes to attach to the body The current geometry is shown below amp Aero Troll v0 2 0b File Edit View Help Components gt 5 Nose Body o 5 Fin Set o C Body o CY Fin Set cS So CDE S The next component which models the horizontal tee tail is a Fin Set component with the following parameters X Shift 12 2876303889 Z Shift 2 0 Body Radius 0 0 Root Chord 1 0 Top Chord 0 5 Span 1 5 LE Sweep 30 0 Fins Only Selected 82 Next delete the fins at 0 and 180 degrees For this case the X Shift requires as many significant figures as possible to insure that the horizontal fin matches up to the tip of the vertical fin The geometry is shown below Aero Troll v0 2 0b File Edit View Help Components gt 5 Nose Body gt CY Fin Set o C Body CY Fin Set gt CY Fin Set This completes the geometry buildup for this example NACA RM L50H08 The following example describes the construction of the wi
67. on the reflected wing will be in the opposite direction T E Flap Roll Def The tailing edge flap deflection for roll control specified in degrees A positive value corresponds to tailing edge down The sum of the absolute value of the trailing edge flap pitch deflection and the absolute value of the trailing edge flap roll deflection must be less than 180 If this wing 43 component is reflected then the trailing edge flap deflection for roll control on the reflected wing will be in the opposite direction Twist in B C A set of radio buttons to determine how the twist will be modeled The choices are to 1 use the setting from the wing 2 model twist in boundary condition 3 model twist physically L E Def In B C A set of radio buttons to determine how the leading edge deflection will be modeled The choices are to 1 use the setting from the wing 2 model the deflection in boundary condition or 3 model the deflection physically T E Def In B C A set of radio buttons to determine how the leading edge deflection will be modeled The choices are to 1 use the setting from the wing 2 model the deflection in boundary condition or 3 model the deflection physically Wedge Currently the intent of the Wedge component is to use it as an independent component which is not physically connected to the Nose Body Body or Fin Set components The origin or the component coordinate system is located halfway along the span of the
68. order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system sRef The reference area used to non dimensionalize the aerodynamic forces and moments The value must be greater than zero IRef The reference length used to non dimensionalize the longitudinal aerodynamic moments The value must be greater than zero bRef The reference length used to non dimensionalize the lateral aerodynamic moments The value must be greater than or equal to zero If the value is equal to zero then IRef will be substituted for bRef 53 xMom The x value for the moment center measured in the local coordinate system Positive is rearward yMom The y value for the moment center measured in the local coordinate system Positive is starboard zMom The z value for the moment center measured in the local coordinate system Positive is up CREATING LINKS A use
69. out the root chord The hinge point transformations are done in the following order 1 The Hinge Cant Angle 2 The Hinge Yaw Angle and 3 Y Shift The hinge point transformations do not effect the wing coordinate system Hinge Line The location of the hinge point origin of hinge line coordinate system along the root chord measured as a fraction of the root chord Incidence Angle Incidence angle of the wing The Incidence Angle and Def Angle parameters have the same effect if the Def In B C checkbox is unselected The incidence angle is always modeled as a physical parameter Def Angle Deflection angle of the wing The Def Angle and Incidence Angle parameters have the same effect if the Def In B C checkbox is unselected If the Def In B C checkbox is unselected the deflection angle will be modeled as a physical angle otherwise it will be modeled in the boundary condition of the analysis method Root Chord The length of the root chord Must be greater than or equal to zero Main Chord Panels The number of panels along the chord between the leading and trailing edge flaps The total number of panels along the wing chord is equal to the sum of the Main Chord Panels L E Flap Panels and T E Flap Panels parameters Root L E Flap Ratio The root chord length of the leading edge flap specified as a fraction of the root chord The value must be between 0 0 and 1 0 inclusive 41 Root T E Flap Ratio The root chord length of
70. r can reference a geometry component from one location to another in the component tree by creating a link To create a link move the mouse cursor over a geometry component and select the geometry component by clicking and holding down the left mouse button The cursor appearance will change to that seen in the figure below or a slash Then drag the component to the desired location in the component tree If the location is an invalid location then the cursor will be a slash otherwise it will be as seen in the figure below In the example shown below my version of a pod racer an AT Analysis component has been created with four Coordinate System components A Group component has been added to the first Coordinate System component and a Nose Body and Fin Set component have been added to the Group component For this case the body length for the Nose Body is zero the number of base panels for the Nose Body is zero the wake for the Nose Body is deactivated the root chord for the Fin Set is set to 1 0 the tip chord for the Fin Set is set to 0 5 the span for the Fin Set is set to 0 5 the Fin Set is shifted back by 2 0 fins 2 through 4 are deleted and the Theta Panels for the remaining fin is set to 12 Next the link is created by left clicking on the Group component and holding down the mouse button Then the Group component is dragged to the second Coordinate System component as shown below and released 54 Aero Troll v0 2 0b File
71. randtl Meyer Tangent Wedge P inf D Tangent Wedge Prandtl Meyer 2 Tangent Cone P inf gt Tangent Cone Prandtl Meyer 9 PANAIR Edit One of six supersonic hypersonic local surface analysis methods can also be chosen The six local surface analysis methods are comprised of a windward and leeward analysis method The selection set of windward methods are 1 modified Newtonian 2 tangent wedge and 3 tangent cone The selection set of leeward methods are 1 po and 2 Prandtl Meyer expansion The impact methods are based on those described in the Mark IV Supersonic Hypersonic Arbitrary Body Computer Program http handle dtic mil 100 2 AD778444 The current set of local surface methods do not account for shielding 14 To modify the values associated with an analysis such as flow conditions and reference values open the Analysis Edit panel by right clicking on the AT Analysis component node and selecting the Edit menu item under the AT Analysis component popup menu The AT Analysis Edit panel for the AT Analysis component is shown below Edit Window alc Nose Body AT Analysis Mach alphac phi AlphaC sRef j IRef xMom i yMom Check PANAIR Edit PANAIR Invalidate Execute Accept All Revert C Revert All 15 Once the required values have been set the solution can be executed b
72. ribution in binary form must reproduce the above copyright notice this list of conditions and the following disclaimer in the documentation and or other materials provided with the distribution Neither the name of Sun Microsystems Inc or the names of contributors may be used to endorse or promote products derived from this software without specific prior written permission This software is provided AS IS without a warranty of any kind ALL EXPRESS OR IMPLIED CONDITIONS REPRESENTATIONS AND WARRANTIES INCLUDING ANY IMPLIED WARRANTY OF MERCHANTABILITY FITNESS FOR A PARTICULAR PURPOSE OR NON INFRINGEMENT ARE HEREBY EXCLUDED SUN MICROSYSTEMS INC SUN AND ITS LICENSORS SHALL NOT BE LIABLE FOR ANY DAMAGES SUFFERED BY LICENSEE AS A RESULT OF USING MODIFYING OR DISTRIBUTING THIS SOFTWARE OR ITS DERIVATIVES IN NO EVENT WILL SUN OR ITS LICENSORS BE LIABLE FOR ANY LOST REVENUE PROFIT OR DATA OR FOR DIRECT INDIRECT SPECIAL CONSEQUENTIAL INCIDENTAL OR PUNITIVE DAMAGES HOWEVER CAUSED AND REGARDLESS OF THE THEORY OF LIABILITY ARISING OUT OF THE USE OF OR INABILITY TO USE THIS SOFTWARE EVEN IF SUN HAS BEEN ADVISED OF THE POSSIBILITY OF SUCH DAMAGES You acknowledge that this software is not designed or intended for use in the design construction operation or maintenance of any nuclear facility Jython 2 2 1 License Copyright c 2007 Python Software Foundation All Rights Reserved PYTHON SOFTWARE FOUNDATION LICENSE VERSION 2
73. roll win script under Windows XP or executing AeroTroll lin under Linux Once Aero Troll is started create the AT Analysis component by right clicking on the working area of Components panel to show the component tree popup menu and then select AT Analysis from the Add menu Once the AT Analysis component is created right click on the AT Analysis component node and select the Edit menu item from the component popup menu to show the AT Analysis edit panel In the At Analysis edit panel set the following parameters to the values given below 68 sRef 7 0686 IRef 3 0 xMom 21 0 Finally click on the Accept button and close the Edit Window The Aero Troll window should look like the following figure Aero Troll v0 2 0b DER File Edit View Help Components 69 Next create a Nose Body component by right clicking on the AT Analysis component node and selecting Nose Body from the Add submenu of the AT Analysis component popup menu Once the Nose Body is created right click on the Nose Body component node to display the Nose Body component popup menu and select the Edit menu item In the Nose Body edit panel set the following parameters to the values given below Include Wake Unselected Nose Type Ogive Nose Radius 1 5 Nose Length 9 0 Body Length 14 4 Body Panels 16 Base Panels 0 After completion the Edit panel for the Nose Body component should look like the following figure 70 Edit Window T
74. s 40 CubicSplineYY ssx 5 6 xl rl dl if ssy 1 0 angle 0 0 else angle ssy 2 0 math pi pp 1 radius math sin angle pp 2 radius math cos angle end of bodySSToPts method 89 beginning of forBodySSToPt method def forBodySSToPt ssx ssy pp if sss oc 0 0 polo 0 0 radius 0 0 elif ssx 1 0 polo xxlA radius yylA else pp L 0 ssx xx1A radius 40 CubicSplineYY pp 0 40 x1 rl dl if ssy 0 0 pp 1 radius pp 2 z 0050 elif ssy 1 0 poli radius pp 2 020 else angle ssy math pi pp i radius math cos angle pp 2 radius math sin angle end of forBodySSToPt method beginning of midBodySSToPt method def midBodySSToPt ssx ssy pp Tf Sse D 0 4 polo xxlA radius yylA elif ssx 1 0 polo xx1B radius yy1B else polo xxlA ssx xx1B xx1A radius 40 CubicSplineYY pp 0 40 x1 rl d1l Lt sy 35 00 poli radius pp 2 0 0 elif ssy 1 0 pp 1 radius pp 2 200 else angle ssy math pi po 1 radius math cos angle po 2 radius math sin angle end of midBodySSToPt method beginning of aftBodySSToPt method def aftBodySSToPt ssx ssy pp if ese gt 0 0 polo xx1B radius yy1B elif ssx 1 0 pp L 0 33 3333 radius 1 6666 2 0 else polo xx1B ssx 33 333 xx1B radius 40 CubicSplineYY pp 0 40 x1 rl d1l if ssy 0 0 poli radius po 2 20 0 elif ssy 1
75. system the second is the deflected wing hinge coordinate system and the third is the wing region root system A wing region is laid out in the wing region coordinate system A wing region coordinate system exists for every wing region of the wing The x axis of wing region coordinate system is aligned with the root chord of the wing region The z axis of the wing region coordinate system is parallel to the normal vector of the wing region before twist is applied The origin of wing region coordinate system depends on whether it belongs to the first wing region the inboard one or one of the remaining wing regions If the wing region coordinate system is for the first wing region then the origin is located at the hinge point of the wing The hinge point of the wing is located on the wing root chord and is a fraction of the root chord rearward from the wing root chord leading edge This fraction is specified by the Hinge Line parameter A Hinge Line value of 0 0 indicates that the hinge point is located at the root chord leading edge and a Hinge Line value of 1 0 indicates that the hinge point is located at the root chord trailing edge If the wing region is one of the remaining wing regions then the origin is located at the twist point of the previous region The twist point of a wing region is located on the wing region tip chord and is a fraction of the tip chord rearward from the tip chord leading edge This fraction is specified by the Twist Loc para
76. t However the load distribution for the Body is presented in the results panel for the Body component The Body component has the following parameters X Shift The amount that this component s coordinate system is shifted backward from the parent coordinate system The value is measured along the parent coordinate system x axis Y Shift The amount that this component s coordinate system is shifted starboard from the parent coordinate system The value is measured along the parent coordinate system y axis Z Shift The amount that this component s coordinate system is shifted upward from the parent coordinate system The value is measured along the parent coordinate system z axis Psi Rot The amount in degrees that this component s coordinate system is yawed The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system 34 Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the parent coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with r
77. t right click on the AT Analysis component and select the Paste menu item A new ForBody Top component will be placed under the AT Analysis component Next rename the new ForBody Top component to ForBody Bot by right clicking on the new ForBody Top component and selecting the Rename menu item The Aero Troll window will look like the following figure Aero Troll v0 2 0b File Edit View Help l Components gt 5 ForBody Top o 5 ForBody Bot 84 To finish the ForBody Bot component set its parameters as follows Phi Rot 180 0 The next set of panel components will be used to define the midsection The methodology is similar to that of building the forebody Create a Panel component and name it MidBody Top Next set the component s parameters as follows Categroy User Defined Function File examples NACA RM L50HO08ScriptsNACA RM L50H08 mid body py Two Sided unselected Chord Panels 5 Span Panels 6 To create the midbody bottom panel copy the MidBody Top component and paste it under the AT Analysis component To do this right click on the MidBody Top component and select the Copy menu item Next right click on the AT Analysis component and select the Paste menu item A new MidBody Top component will be placed under the AT Analysis component Next rename the new MidBody Top component to MidBody Bot by right clicking on the new MidBody Top component and selecting the Rename menu item Next s
78. the edge 1s Selecting the buttons is identical to selecting or unselecting all the Edg1 check boxes Edge 2 Show Hide All Show or hide all the edge 2s Selecting the buttons is identical to selecting or unselecting all the Edg2 check boxes Edge 3 Show Hide All Show or hide all the edge 3s Selecting the buttons is identical to selecting or unselecting all the Edg3 check boxes 31 Edge 4 Show Hide All Show or hide all the edge 4s Selecting the buttons is identical to selecting or unselecting all the Edg4 check boxes Network and Abutment visibility check box table Please see the Checking PANAIR Abutments section for a description of these check boxes Geometry The Geometry base component is a geometry container class for geometry components This component has no parameters The Geometry base component accepts geometry components just as the AT Analysis component does but unlike the AT Analysis component it does not associate the attached components with one or more analysis methods The Geometry base component is a convenient storage location for complex geometries comprised of multiple sub geometries Nose Body The Nose Body component is an axisymmetric geometry which has either a cone or ogive nose After executing the analysis method for this component the final integrated loads and moments are shown in the results panel of the base component However the load distribution for the Nose Body is presented in the results
79. the terms and conditions of the Aero Troll license select the About menu item under the Help menu Problem Specification The guiding principle behind the design of Aero Troll is to create an aerodynamic analysis system based on a component buildup approach which allows a user to quickly experiment with a variety of geometries and analysis approaches The goal is to create a tool which predicts preliminary aerodynamics for a given geometry and to create a tool which can be used to determine the strengths and weaknesses of analysis methods An additional goal for Aero Troll is to run on desktops laptops and high end workstations under a variety of operating systems To summarize the usage the user creates an analysis base component and then populates the analysis base component with geometry components Flow conditions and reference values are then specified for the analysis base component and analysis methods are chosen for the components Finally the user executes the analysis base component and views the results The remainder of this section will give a brief example of this process The sections which follow discuss the geometry components in more detail and give further examples To start the process the user creates an analysis base component and adds it to the component tree by right clicking in the white portion of the Components panel and then selecting the AT Analysis menu item under the Add submenu of the component tree popup me
80. the trailing edge flap specified as a fraction of the root chord The value must be between 0 0 and 1 0 inclusive L E Flap Panels The number of panels along the chord of the leading edge flap The total number of panels along the wing chord is equal to the sum of the Main Chord Panels L E Flap Panels and T E Flap Panels parameters T E Flap Panels The number of panels along the chord of the trailing edge flap The total number of panels along the wing chord is equal to the sum of the Main Chord Panels L E Flap Panels and T E Flap Panels parameters Def In B C If selected the wing deflection will be modeled in the boundary condition Twist In B C If selected the twist will be modeled in the boundary condition by default The default twist modeling can be overridden on a region by region basis L E Def In B C If selected the leading edge deflection will be modeled in the boundary condition by default The default leading edge deflection modeling can be overridden on a region by region basis T E Def In B C Tf selected the trailing edge deflection will be modeled in the boundary condition by default The default leading edge deflection modeling can be overridden on a region by region basis More Display the advanced settings dialog The following input parameters are for a wing region Each wing region represents a set of panels laid out between a root and tip chord The regions are then connected end to end
81. the wake will follow along the x axis of the global coordinate system Fin Wake f selected wake panels for the fins will be included in the PANAIR calculation Body Radius The radius of the body The value must be greater than zero Root Chord The root chord for the fins The value must be greater than zero Tip Chord The tip chord for the fins The value must be greater than or equal to Zero Span The span for the fins The value must be greater than or equal to zero Is L E Sweep If selected the fin sweep is specified by the leading edge Otherwise the sweep is specified by the trailing edge L E T E Sweep The leading edge or trailing edge sweep for the fins Hinge Line The hinge line location as a function of the percentage of the root chord Note that the hinge line is perpendicular to the surface Chord Panels The number of panels along the chord of the fin and along the length of the body The value must be greater than zero Span Panels The number of panels along the span of the fin The value must be greater than zero Base Panels The number of panels on the base along the radius The value must be greater than or equal to zero If the value is zero then a base will not be included Fins Only If selected the body will not be included Def In B C If selected the deflection will not be modeled physically but applied to the boundary conditions of the analysis method The resulting integrated force and
82. tios If selected the leading edge flap tip ratio and the trailing edge flap ratio will be copied from the previous region or the wing flap root ratios L E Flap Tip Ratio The tip chord length of the leading edge flap specified as a fraction of the tip chord The value must be between 0 0 and 1 0 inclusive T E Flap Tip Ratio The tip chord length of the trailing edge flap specified as a fraction of the tip chord The value must be between 0 0 and 1 0 inclusive L E Flap Pitch Def The leading edge flap deflection for pitch control specified in degrees A positive value corresponds to leading edge up The sum of the absolute value of the leading edge flap pitch deflection and the absolute value of the leading edge flap roll deflection must be less than 180 T E Flap Pitch Def The trailing edge flap deflection for pitch control specified in degrees A positive value corresponds to trailing edge down The sum of the absolute value of the trailing edge flap pitch deflection and the absolute value of the trailing edge flap roll deflection must be less than 180 L E Flap Roll Def The leading edge flap deflection for roll control specified in degrees A positive value corresponds to leading edge up The sum of the absolute value of the leading edge flap pitch deflection and the absolute value of the leading edge flap roll deflection must be less than 180 If this wing component is reflected then the leading edge flap deflection for roll control
83. transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the global coordinate system Tht Rot The amount in degrees that this component s coordinate system is pitched The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the global coordinate system Phi Rot The amount in degrees that this component s coordinate system is rolled about The rotation transformations are applied in the same order as the aircraft Euler angle system i e yaw pitch and then roll and are with respect to the global coordinate system Mach The Mach number for the analysis Gamma The ratio of the specific heats Flow Angle Specification The drop down selection box allows the user to choose one of five methods to enter the free stream flow angle 1 alphac phi ac q 29 where u V XCOSL0d 1 v V sin ac sin q w V sin a cos Q 2 sin sin ds Bs where sin ds W V sin Bs v V o Note that the u velocity is ambiguous when both as and p are greater than 90 Therefore it is assumed in this formulation that the intent of B is to be in the range of 90 degrees 3 tan tan a By where tan o 7w u tan B 7 v u This form is indeterminate when both a and f are equal to 90 degrees 4 tan sin o Bs where tan o w u sin Bs v V v 5 u v W sRef
84. ts to a body segment edge 100 degrees a panel network for the wake was not created This can be seen in the image above for the starboard wake 64 3 Physical deflections should be used with caution Physical deflections cause two problems for PANAIR First a fin panel may have excessive influence on a body panel control point since the fin panel edge may be too close to a body panel control point Second the wake will not attach itself to a body edge segment This is shown in the figure below for a 20 degree deflection of the starboard fin In the figure above it can be seen that the root edge of the fin panel network passes close to the body panel control points It can also be seen that the fin wake is not attached to the body and therefore odd panel strengths may result When using PANAIR the deflections for the fins should be handled by the boundary conditions This is specified by selecting the Def In B C checkbox 65 4 Wakes should not intersect panels If panels intersect or overlay one another then the results will be indeterminate or incorrect Two examples of wakes intersecting panels are given The first example is of a wake from a forward fin intersecting a rear fin This is shown in the figure below In this example the rear fins were shifted down by two degrees and then given an upward dihedral of 10 degrees If the rear fins were actually in the plane of the wake a warning would have been given that Mu
85. wake panels will be included in the PANAIR calculation Local Wake If selected the wake will follow along the x axis of the parent coordinate system otherwise the wake will follow along the x axis of the global coordinate system Nose Type A radio button grouping for selecting either a Cone or Ogive nose Nose Radius The maximum radius of the nose Nose Length The length of the nose Measured parallel to the local x axis from the nose tip to the shoulder This value must be greater than zero Body Length The length of the body Measured parallel to the local x axis from the shoulder to the base The value must be greater than or equal to zero Tip Radius The nose tip radius The value must be greater than or equal to zero Nose Droop The droop of the nose Measured parallel to the local z axis Tip Panels The number of panels laid out along the nose tip center line from the forward point of the nose tip to the junction of the nose tip and nose The value must be greater than zero Nose Panels The number of panels laid out in the axial direction from the junction of the nose tip to the shoulder The value must be greater than zero Body Panels The number of panels laid out in the axial direction from the shoulder to the base The value must be greater than zero Base Panels The number of panels on the base along the radius The value must be greater than or equal to zero If the value is zero then a base will not be included
86. wed from the back towards the front The value is in degrees Deflection The deflection of the fin A positive deflection is leading edge up when viewed looking outward along the hinge line The value is in degrees Include Body If unselected panels will not be laid out on the body segment Theta Panels The number of panels in the theta direction for this segment The value must be greater than zero Wing The Wing component is used to model wings The wing planform is modeled by regions where each region has straight leading and trailing edges and straight root and tip chords The number of chordwise panels for all the regions is constant whiles the number of spanwise panels for the regions can vary from region to region The wing component can model twist and leading and trailing edge flaps The current version of the wing component does not model thickness or camber 38 Each wing has a true and paneled geometry associated with it If any deflection or twist is modeled in the boundary condition then the deflection and twisted will be incorporated in the physical geometry layout of the true geometry and will not be incorporated in the layout of the paneled geometry For the analysis the paneled geometry is used to determine the pressures The pressures are then transferred to the true geometry and the loads are calculated There are three coordinate systems associated with the wing component The first is the wing component coordinate
87. xl rl d1 0 0 calculate wing corner locations cc1 20 5 5 quarter chord location at centerline cc2 20 6 5 d quarter chord location at wing tip XX1A cc1 0 25 7 5 yylA 0 0 xx1B ccl 0 75 7 5 yy1B 0 0 XX2A cc2 0 25 4 5 yy2A 12 0 XX2B cc2 0 75 4 5 yy2B 12 0 calculate intercept of wing leading edge with body xi xxlA initial guess dywdx yy2A yylA xx2A xx1A slope for wing while 1 yw yylA dywdx xi xx1A yb 40 CubicSplineYY xi 40 0 x1 rl dl dy yw yb dybdx CubicSplineDY xi 40 0 xl rl dl dx dy dybdx dywdx xi xi dx if math fabs dx 1 0e 14 break set values yylA yylA dywdx xi xx1A xx1A aci calculate intercept of wing tail edge with body xi xx1B initial guess dywdx yy2B yylB xx2B xx1B slope for wing while 1 yw yylB dywdx xi xx1B yb 40 CubicSplineYY xi 40 0 x1l rl dl dy yw yb dybdx CubicSplineDY xi 40 0 xl rl dl dx dy dybdx dywdx Sea xi dx if math fabs dx lt 1 0e 14 break set values yy1B yy1B dywdx xi xx1B xx1B xi HHHHHHHE ending of NACA RM L50H08 py script HEFHHHH beginning of NACA RM L50H08 for body py script import math from examples NACA RM L50H08 Scripts import NACA RM L50H08 reload NACA RM L50H08 def ssToPt ssx ssy pp NACA RM L50H08 forBodySSToPt ssx ssy pp HHHHHHHE ending of NACA RM L50H08 for body py script
88. y selecting the Execute button The contour plot for the pressure non dimensionalized by the free stream pressure will be shown in the Main Display panel File Edit View Help Components o 5 Nose Body 16 Select the Results button in the AT Analysis Edit panel or the Results menu item in the AT Analysis component popup menu to view the integrated results s The AT Analysis Results panel which is contained in the Result window is shown below Result Window AT Analysis AeroTroll Version 0 2 0b Coordinate System Notes Unless specified otherwise CX is positive back CY is positive starboard CZ is positive up Cl is positive right wing down Cm is positive nose up Cn is positive nose to the starboard AT Analysis Class AT nalysis Mach 0 5 Gamma 1 4 Flow angle type alphac phi AlphaC 0 0 Phi 0 0 Ref Area 1 0 Lat Ref Len 1 0 Views The base component must be activated to view it in the Main Display panel Only one base component can be active at a time Select the Activate or Deactivate menu item from the base component popup menu to activate or deactivate the base component The Main Display panel allows the user to translate rotate and zoom in and out To translate the image hold down the left mouse button and move the mouse in the direction the image should be translated To rotate the image hold down the right mouse button and move the mouse

Aero Troll - Hegedus Aerodynamics

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