CIRA-CF-09
Contents
1. 14 REFERENCES 15 Page 2 of 15 ha 1 0 INTRODUCTION Since September 1998 CIRA the Italian Aerospace Research Centre has entered into operation a Transonic Wind Tunnel PT 1 with the aim to support industrial and research programmes with a versatile and high flow quality aerodynamic testing platform over a wide speed range for a variety of small scale test articles In May 2000 CIRA has been granted membership in the Supersonic Tunnel Association International STAI This document describes the wind tunnel technical characteristics and performances its instrumentation and the typical operative procedures The CIRA PT 1 is equipped with complete tunnel instrumentation for aerodynamic measurements CIRA test engineers are available for measurement support and data interpretation Nevertheless customers are free to operate within their individual agreement with CIRA their own instrumentation The facility is located in Capua CE Italy about 50 km north of Naples The Transonic Wind Tunnel is part of a brand new complex which includes ground testing facilities and dedicated service utilities making up the Italian Aerospace Research Centre The picture Fig 1 shows a view of the facility Fig 1 Transonic Wind Tunnel PT 1 General Overview CIRA CF 09 1144 PT1 USER MANUAL 2 0 LIST OF ACRONYMS CIRA Centro Italiano Ricerche Aerospazia2. Ejector primary air pressure 15 4 bar 10 0 FACILITY MANAGEMENT SYSTEM The CIRA PT 1 wind tunnel is equipped with two systems managing data coming from the field Control System CS Data Acquisition System DAS DAS ENG PC PC Elsag Bailey Data Highway Dedicated Allen Bradley Control PSI SLC500 System Unit PLC Air Supply i System Instrumentation i CircuitExhaust Facilit Instrumentation Instrumentation Instrumentation Dr NN PT 1 Wind Tunnel Fig 15 Facility Management System 10 1 TUNNEL CONTROL SYSTEM CS gets data from the field in order to control the facility see fig 16 The Master Control System MCS is a digital control system which consists of a run console servo controllers instrumentation The process is controlled by the MCS The MCS includes a ELSAG BAILEY INFI 90 and LAN 90 control system Page 11 of 15 INFI90 Fig 16 Control System functional Diagram The Control System has two types of control loops that process control loops and the positioning control loops Control loops are used to control the tunnel injector and ejector pressures Position con
3. 2D 0 1 m q 2 500 Pa q 5 000 Pa Re q 10 000 Pa q215 000 Pa q 30 000 Pa 3 000 000 50 000 Pa q 60 000 Pa Lref 3D 0 040 2 500 000 4 ao NES n 2 000 000 1 500 000 1 000 000 4 500 000 4 Fig 4 PT 1 operating envelope Reynolds vs Mach number Lref 0 1 m Re 500 000 4 750 000 1 000 000 90 1 Re 1 250 000 Re 1 500 000 Re 1 750 000 Re 2 000 000 Rez2250 000 Re 2 500 000 Re 2 750 000 Re 3 000 000 11 12 12 14 15 Fig 5 1 operating envelope Total pressure vs Mach number The Mach number distribution in the empty test section has been measured during facility calibration using a centreline static pipe The mach distribution is shown in fig 6 CIRA CF 09 1144 PT1 USER MANUAL 1 Model Length 100 200 300 400 500 Test section length mm Fig 6 Empty tunnel Mach number longitudinal distribution 5 0 TEST SECTION DETAILS The facility is equipped with two test sections one for subsonic tests and the second for transonic supersonic tests wit
4. Sweep test modes In Fig 17 the overall system configuration is illustrated The integrated hardware devices are a An electronically pressure scanning system PSI8400 which acquires about 250 pressure measurements on the model and on the wind tunnel internals This system is connected to the controller PC through a IEEE488 link b A high precision barometer DPI740 for the precise measurement of the atmospheric pressure This device is connected to the controller PC through a RS232 link c A dual sensor RUSKA6222 for high precision Mach number measurement This device is connected to the controller PC through a RS232 link d A computer based turn table system for model attitude positioning This device is connected to the controller PC through a RS232 link Controller PX E 4 x tt AS 232 m mM RUSKA 6222 Integrator PC Ethernet r Turn Tables Fig 17 PT 1 Data Acquisition System Configuration Page 12 of 15 ha 11 0 COMPUTER PLATFORM The host hardware platform is based on a PC network running Microsoft Windows XP The communication is assured by an 100 Mbit Ethernet LAN The interface to the PLC based low level control systems consists of an industrial Ethernet LAN Moreover the 1 computer network consists of the following PC File server Tunnel control host Test automation host of the equipment following data
5. acquisition Pressure System Balance System The following devices are also available B W Laser printer Video system All systems are fed through UPS supply 12 0 TEST GENERAL ARRANGEMENT The facility in principle runs on a single shift of 8 hours per day but on request different working time can be contracted The time required for a run is strongly affected by the measurements to be performed after the run The PT 1 is charged on occupancy time basis with no regard to actual test conditions No difference is made also for test or after run inspection nor for configuration changes when needed The model preparation is normally made outside of the wind tunnel in the model preparation room Model preparation is usually quoted fixed time plus material basis CIRA can arrange for test model instrumentation and manufacturing agreed with sufficient time in advance Normal complexity models will require 6 months for design and construction by CIRA CF 09 1144 PT1 USER MANUAL CIRA Quotation can be given on request Model supplied by customers shall be verified A stress analysis report shall be performed including thermal stresses dynamic stresses cyclic stresses Model and user instrumentation interfaces shall be clearly identified and agreed between PT 1 user and CIRA PT 1 test engineers In case special parts are needed to accommodate actual interfaces either CIRA or PT 1 user can provi
6. DOCUMENT NUMBER CIRA CF 09 1144 DISTRIBUTION STATEMENT WP NATURA DOCUMENTO RISTRETTO COND_LMSA 3090510000 9051 ARCHIVIO ROGRESSIVO DI ARCHIVIO NO OF PAGES DELIVERABLE CIRA PTUN 0047 TITLE CIRA PT 1 USER MANUAL PREPARED REVISED APPROVED AUTHORIZED PREPARATO VERIFICATO APPROVATO AUTORIZZATO Izzo Carmelo Izzo Carmelo Izzo Carmelo Vecchione Ludovico SIAE DATE DATA DATE DATA DATE DATA DATE DATA 14 09 2009 14 09 2009 14 09 2009 14 09 2009 BY THE TERMS OF THE LAW IN FORCE ON COPYRIGHT THE REPRODUCTION DISTRIBUTION OR USE OF THIS DOCUMENT WITHOUT SPECIFIC WRITTEN AUTHORIZATION IS STRICTLY FORBIDDEN A NORMA DELLE VIGENTI LEGGI SUI DIRITTI DI AUTORE QUESTO DOCUMENTO DI PROPRIETA CIRA E NON POTRA ESSERE UTILIZZATO RIPRODOTTO O COMUNICATO A TERZI SENZA AUTORIZZAZIONE DOCUMENT NUMBER CIRA CF 09 1144 TITLE CIRA PT 1 USER MANUAL ABSTRACT The present document describes the characteristics and the procedures of the CIRA Transonic Wind Tunnel PT 1 The PT 1 performance and the main dimension are described The PT 1 auxiliary systems have been described The time schedule requirements and the support requirement have been also outlined in order to give a guideline to PT 1 test organization and facility reservation Furthermore the CIRA location and nearest lodging options have been presented AUTHORS Izzo Carmelo Martire Luigi APPROVAL REVIEWERS Izzo Carmelo APPROVER Izzo Carmelo AUTHORIZATION R
7. ER INSTRUMENTATION ra 9 9 4 24 eene e iu pii Dee Noe eese tiene t 9 8 5 IMAGING CAPABILI Y 9 8 6 MODEL SUPPORT SYSTEM 55 9 9 7 INTERNAL 9 8 7 1 3 Component Strain Gage Balance Characteristics 9 8 7 2 6 Component Strain Gage Balance Characteristics 10 9 0 AUXILIARY SYSTEMS siii idilliaca 10 9 1 AIR SUPPLY SYSTEM 10 9 2 IRCO MAU lit 11 9 3 PLENUM rollio 11 10 0 FACILITY MANAGEMENT SISTEM Gira 11 10 1 TUNNEL CONTROL 11 10 2 DATA ACQUISITION AND ELABORATION 5 12 11 0 COMPUTER PLATFORM uiis dea 13 12 0 TEST GENERAL ARRANGEMENT 13 13 0 PIT OPERATING TEAM scia 13 14 0 PERSONNEL SAFETY 550 5 1 13 di HAA 13 147 alii 14 Page 1 of 15 E IRA CIRA CF 09 1144 PT1 USER MANUAL 14 3 15 0 16 0 17 0 18 0 EMERGENCY PROCEDURES illa 14 CIRASIFELOGISHCO c E E E 14 PT 1 TEST REQUEST PROCEDURE 14 CONTAC T
8. EVIEWERS Vecchione Ludovico AUTHORIZER Vecchione Ludovico II DOCUMENT NUMBER CIRA CF 09 1144 DISTRIBUTION RECORD Gruppo Ptun PT PARTIAL A ALL DOCUMENT NUMBER CIRA CF 09 1144 IDENTIFICATIVO REV REVISION LIST LISTA DELLE REVISIONI REV DESCRIPTION DATE EDITOR m Sostituisce CIRA UM 04 3 Aeiornata Lisa Contact Point 4092009 E IRA CIRA CF 09 1144 PT1 USER MANUAL SUMMARY 1 0 annus 3 2 0 LIST OF 65 3 3 0 FACILITY 3 3 1 GENERAL 2 000 0 0 0 6 0 3 4 0 TUNNEL OPERATION 4 4 1 PT 1 AERODYNAMIC PERFORMANCE eene nennen 4 5 0 SECTHON DETAILS ia 5 6 0 FAN SYSTEM andina 6 7 0 COOLINGSTtSEEM iii 6 8 0 6 9 1 II a ne 6 9 2 PRESSURE MEASUREMENT INSTRUMENTATION enm 7 8 3 OTH
9. F 09 1144 PT1 USER MANUAL Top and bottom fore zones have a rectangular longitudinal section 6 0 mm thick an internal cavity 2 0 mm wide has been provided corresponding to the minimum dimension that allow the installation of total pressure probes and the routing of the relevant connection tubes The need for a larger central zone stems from the necessity to install 46 Pitot probes 21 of them are placed along the central longitudinal section 19 along 2 lines placed symmetrically at a distance of 2 5 mm from the central section and 6 along 2 more lines placed symmetrically at a distance of 5 mm from the central section The pitot probe distribution allows to capture the whole wake event at incipient Stall conditions Fig 10 Wake Rake Installed on 1 model support system configuration 8 2 PRESSURE MEASUREMENT INSTRUMENTATION Pressure is the main parameter measured in PT 1 The facility is equipped with two pressure measurement systems Page 7 of 15 ha The first system is part of the Master Control System MCS dedicated to the control of the facility This system is equipped with two absolute pressure transducers for the measurement of total pressure in stilling chamber and static pressure in plenum chamber and two differential pressure transducers to measure dynamic pressures The table 2 shows the characteristics of these transducers which are critical to assess the facility operat
10. Suitable signs are located in critical areas nevertheless PT 1 users are not allowed to operate any facility component During the pre test meeting the potential hazard will be showed and discussed PT 1 users will also be informed about safety procedures before the test program start 14 2 PROTECTIVE EQUIPMENTS Impact protection helmets and noise protection taps can be found in 1 building Other personal equipment needed for workshop activities will not be provided by CIRA The PT 1 users will be provided with their own personal protection devices such as working gloves shoes to be used for model mounting and assembly in the model preparation area 14 3 EMERGENCY PROCEDURES The CIRA emergency procedure will be showed to PT 1 users All necessary protection devices will be provided to guests care of CIRA If required all people in the PT 1 area shall follow CIRA team safety responsible instruction 15 0 CIRA SITE LOGISTIC CIRA is located in Capua a small town near Naples and Caserta located at about 200 kilometers south of Rome and about 50 Kilometers North of Naples Customers can arrange their trip to CIRA with a flight either to Rome Fiumicino Airport or to Naples Capodichino Airport 16 0 PT 1 TEST REQUEST PROCEDURE To perform tests in PT 1 a formal request has to be submitted at least one year in CIRA CF 09 1144 PT1 USER MANUAL advance of the scheduled date for testing to CIRA The request
11. alls below the set point the valves close slightly as required to gain pressure The exhaust air is drawn out of the tunnel through a perforated section collects in a plenum and flows through four exhaust ducts to the circuit exhaust stack The exhaust system characteristics are Maximum mass flow rate 21 kg sec Maximum system pressure 1055 control valves fully open lt 0 20 bars Exit pressure 1 0 bars Minimum inlet pressure to be determined from PT 1 operation 9 3PLENUM EXHAUST The plenum exhaust system PES is used to extract up to 3 of the wind tunnel mass flow through the perforated walls of the transonic test section The PES controls the test section conditions at transonic Mach numbers up to 1 05 The PES trims the test section conditions at Mach 1 4 Two symmetrically placed exhaust ducts are used one on each side of the test section plenum to reduce the impact of the plenum exhaust flow on the test section flow quality Each exhaust duct contains a butterfly valve for controlling the plenum pressure using closed loop control An ejector downstream of the control valves pumps CIRA CF 09 1144 PT1 USER MANUAL the plenum exhaust to the exhaust stack at atmospheric pressure The ejector is driven by the air supply system The plenum exhaust system characteristics are Maximum wall flow removal rate 1 9 kg sec Minimum plenum pressure 0 47 bar Maximum ejector primary flow 4 73 kg sec
12. cution shall also be sent to CIRA for PT 1 area entry permit preparation 17 0 CONTACT POINT The CIRA mail address is Page 14 of 15 ha CIRA scpa Via Maiorise s n c 81043 Capua CE ITALY The CIRA responsible for Aeronautical Ground Test Facilities is Ing Ludovico Vecchione Phone 39 0823 623918 Fax 39 0823 969272 E mall I vecchione cira it The CIRA responsible for PT 1 Wind Tunnel is Ing Carmelo Izzo Phone 39 0823 623013 Fax 39 0823 969272 E mail c izzo cira it Secretary 39 0823 623963 Fax 39 0823 969272 CIRA Operator 39 0823 623111 CIRA entrance desk 39 0823 623001 18 0 REFERENCES 1 Ferrigno F Fusco F Manco M De Matteis P CIRA Transonic Wind Tunnel PT 1 Performance Analysis CIRA TM LAS 99 175 2 Ferrigno F Manco M Ragni A Transonic Wind Tunnel Aerodynamic Commissioning MC 3C CIRA 7 TN 0074 3 Fauci R Imperatore B Design Realisation and Performance Evaluation of a High Accuracy Wake Drag Measurement Device for Cira Transonic Wind Tunnel 4 Inverno M Fusco F A PC Based Data Acquisition System Supervisor 19 International Congress Instrumentation in Aerospace Simulation Facilities ICIASF 01 CIRA TN 01 0156 CIRA CF 09 1144 PT1 USER MANUAL 5 D Alessandro L Descrizione del sistema Acquisizione Dati della Galleria del Vento Transonica Pilota MC 3C CIRA 7 MO 0029 6 Fauci R Imperato
13. de them as agreed during the test preparation meeting in the contractual phase The customer are allowed in the control room with its own instrumentation and all cabling can be routed through the shell penetration to the model in the test section The cable length for instrument connection shall be at least 12m On request the use of computer with analysis SW can be arranged during the test session and in general CIRA test engineer available for data interpretation and technical discussion A test report containing all the images video and measurements performed will be issued at the end of the experimental activity for the customer In case joint publications can be issued after the test campaign a reciprocal authorization will be signed for data communication to third parties 13 0 PT 1 OPERATING TEAM The facility is operated and maintained by a dedicated support team which can be integrated with other specific competence currently available in CIRA The department is currently hosting 3 Test Engineers one Facility Operator under supervision of a Laboratory Manager 14 0 PERSONNEL SAFETY ISSUES 14 1 HAZARDS Some potential hazards can be taken into account during test preparation and execution due to the variety of systems running in the PT 1 area The main are listed below Page 13 of 15 ha High pressure pipe Electrical shocks Laser light exposure Mechanical hazards
14. ections 9 1 AIR SUPPLY SYSTEM The air supply system provides air to drive the tunnel injector and the plenum ejector for intermittent operations in the transonic range The system includes an air compressor system high pressure air storage tanks and piping to deliver air to the injector nozzles and the plenum ejectors The supply system characteristics are Pressure at injector 17 bar absolute Maximum injector mass flow rate 21 kg sec Maximum plenum ejector flow rate 5 kg s Runtime at Mach 1 4 130 sec Minimum air temperature 10 C Maximum temperature excursion during a run 10 C from tunnel ambient Maximum storage repump time 30 minutes Page 10 of 15 ha 9 2 CIRCUIT EXHAUST The function of the circuit exhaust system is to remove the air added to the circuit by the injector To overcome the aerodynamic losses in the piping and exhaust stack the tunnel pressure at the exhaust location must be somewhat above ambient in order to be driven out of the circuit without the aid of external pumping To accomplish this at the 1 transonic operation the minimum tunnel pressure will be in the range from 1 25 to 1 5 bars The actual value will be determined from the pilot test program The circuit exhaust system control valves operate in a closed loop control mode If the tunnel pressure rises above the set point the valves open slightly as required to release pressure If the pressure f
15. h perforated walls 60 inclined holes 6 3 porosity Both test sections have floor and ceiling adjustable walls 0 5 deg In the intermittent injection driven operation mode the Mach number set point is in the range between 0 4 and 0 8 reached via the 2nd throat adjustment while for higher Mach numbers the set point is reached via mass flow removal up to 3 of the overall circuit mass flow on the test section perforated walls The different test section features are listed in Tab 1 Fig 7 Solid wall test section Page 5 of 15 ha Test section Transonic Parameter Supersonic Size w h l 350x450x600 350x450x600 Walls Solid 6 porosity Contraction 1 Test section features Test sections are equipped with lateral inserts for 2D and half model testing The 2D TS insert provides the means to gain aerodynamic data from articles spanning between the side walls Three assemblies form the mechanical hardware one far and one near side wall assembly nearest respectively furthest to the control room plus one floor assembly Each of the side wall assembly consists of a rigid base frame to which a turn table together with a machinery and drive components is attached 6 0 FANSYSTEM The fan Fig 8 provides the motive power to the wind tunnel during continuous subsonic operations at Mach numbers up to 0 4 It is connected to an 132 kW external drive motor and has both conti
16. including the target test period number of runs type of experiment test article description and the measurement to be performed will be examined and preliminary meeting should be organized to discuss the test detail and scheduling Within one month from the meeting the test program detail and scheduling will be defined and a Statement Of Work SOW will be submitted to the PT 1 user along with the related project cost After the PT 1 test contract formalization and signing by both parties the preparatory work can be scheduled between CIRA 1 engineer and the customer During this test preparation activity one or more meeting will be dedicated to Test plan definition Model mounting detail Instrumentation definition and related connection PT 1 configuration Auxiliaries system requirements Data acquisition and reduction At least 6 moths in advance the PT 1 user shall supply to CIRA all the detail about the model mounting interface necessary connection as well as the report on the stress analysis and electromagnetic compatibility If model design and construction has been assigned to CIRA a design review meeting will be organized at the same date to freeze the model configuration Two weeks before the scheduled test date the PT 1 user shall deliver to CIRA the test model its instrumentation and all the relevant interface A list of user personnel attending test preparation and or exe
17. ion Page 6 of 15 ha is obtained corresponding to the maximum allowable rear position Fig 9 Fig 9 Long and Short configurations Central body is interchangeable interface element between the fore body and the rear support By substituting with a new piece or omitting this part it is possible to vary the longitudinal position of the probe array Central body can be installed or removed from the wake rake system without removing probe connection tubes A removable cover panel located on one side in the central zone allows the access to the central internal vane provided for tube driving Rear support and fore body are the base elements of the wake rake system Rear Support is the interface with wind tunnel arc sector support system its shape has been designed in order to satisfy the installation requirement and reproduces where possible the existing conical arc sector The fore body is the core of the wake rake system designed to allow the installation of 64 total pressure probes and four supports for static pressure probes It consists of 3 subcomponents 2 of them fixed together after machining and resulting in a main fore element the third one is a removable cover element allowing the access to the internal cavity Fore body central zone has a cuneiform shape varying from a rectangular rear end section 16 mm wide to a forward section with a 3 0 mm diameter rounded shape CIRA C
18. ion condition Parameters from those transducers may be used for understanding of the aerodynamic process inside major facility components Measured Accuracy Abs Error Parameter Bar Total pressure in stilling chamber Static pressure in plenum chamber Dynamic Pressure low Dynamic Pressure high range Tab 2 MCS Pressure Transducers characteristics The second system is the PSI 8400 manufactured by Pressure System PSI 8400 is part of the test data acquisition system Pressures data collected duringA run may be acquired by means of the PSI 8400 Fig 11 The pressure transducers characteristics are shown in tab 3 CIRA CF 09 1144 PT1 USER MANUAL Measured FS Accuracy ti Parameter PSI F S Bar Pt and PS in stilling 30 0 05 1E 03 Differential chamber Ps on the centerline 0 05 5E 04 Differential 0 05 1E 03 Differential Tab 3 PSI 8400 pressure transducers characteristics Fig 11 PSI 8400 system 8 30THER INSTRUMENTATION Other available instruments for flow characterization are Hot Wire Flow Angularity Probe Page 8 of 15 8 4 VIRTUAL INSTRUMENTATION In case necessary for a specific test other instruments can be connected to FMS system The FMS will recognize these instruments as Virtual Instruments Particularly the connection can be performed linking physically and logically the instrument to Data Acquisition System The logical link is
19. li CL Wind Tunnel Centre Line CS Cooling System DAS Data Acquisition System FMS Facility Management System HX Heat Exchanger HW Hardware PT 1 Pilot Tunnel 1 MSS Model Sting Support SW Software TS Test Section UPS Uninterruptable Power Supply Velocity VI Virtual Instrumentation WT Wind Tunnel 3 0 FACILITY DESCRIPTION 3 1 GENERAL DESCRIPTION The Transonic Wind Tunnel 1 is closed circuit pressurised wind tunnel A sketch of the PT 1 functional layout is shown in Figure 2 i Si BRE6RIF ds ev FAUST s E ORON DINAUST VALES an LL RERUM a ERAST T 1 LT SENT VALE PLAN at iy FAM DRE Fig 2 Transonic Wind Tunnel PT 1 functional layout The PT 1 has two drive systems a fan for continuous subsonic tests and an air compressed system for intermittent transonic and supersonic tests The facility is equipped with two nozzle blocks a convergent nozzle for Mach numbers below 1 1 including fan continuous operations and a convergent divergent nozzle for intermittent operations at M 1 4 Page 3 of 15 ha Two test sections are available one with solid walls for subsonic tests and the other one with perforated walls for transonic tests Both the test sections have top and bottom adjustable walls a 0 5 deg Lateral wall inserts for 2D and half model testing are also available The inserts are equipped with bottom and side walls optical window
20. nnel may be operated is 1 75 bar The Mach number is variable from 0 4 to approximately 1 05 using convergent nozzle blocks Operation at Mach 1 4 is achieved using convergent divergent nozzle blocks For Mach numbers from 0 4 to approximately 0 8 Mach number is controlled using the second throat and the Mach trim on the second throat centerbody For Mach numbers between 0 8 and 1 05 and at Mach 1 4 Mach number is controlled by varying plenum pressure using the plenum exhaust flow system with the second throat at a fixed position While subsonic operation is in continuous mode the transonic and supersonic operation is intermittent with a maximum run time of about 130 sec 4 1 1 AERODYNAMIC PERFORMANCE In the transonic and the supersonic tests the test section wall angles have been set to a diverging angle of 0 25 deg to control the boundary layer growth along the walls The main performance parameters of the PI 1 wind tunnel have been included in tab 1 Fig 4 shows the operating envelope of the wind tunnel in terms of achievable Mach amp Reynolds for both 3D and 2D models Reference lengths are 10 of the square root of the test section area and a 2D chord of 10 cm Fig 5 Page 4 of 15 ha shows the envelope with Reynolds curves for the 2D reference length 3 500 000 4 Q 7 500 Pa Q 20 000 Pa 40 000 Pa Lref
21. nuous adjustable blade pitch and variable speed n max 3000 rpm in order to achieve the most efficient layout over the entire subsonic Mach range During transonic operations with the injector drive system the rotor blades ere locked in a fixed position to perform tests of the optimum operating conditions which minimizes losses through the fan CIRA CF 09 1144 PT1 USER MANUAL Fig 8 Fan Unit and injectors system The wind tunnel speed is automatically controlled via the Facility Management System FMS 7 0 COOLING SYSTEM The Cooling System CS function is to remove the heat generated by the fan during continuous operations Cooling water flow is variable up to 5 It s A heat exchanger dissipates the energy delivered to the stream by the wind tunnel drive fan The heat exchanger is designed for low pressure loss spatially uniform flow and small variations in bulk air temperature across its face The main characteristics of the heat exchanger are Water inlet temperature 12 8 C Water flow rate 3 011 5 2 11 Removed heat 50 kW 8 0 INSTRUMENTATION 8 1 WAKE RAKE A wake rake for drag measurement in the CIRA transonic wind tunnel PT 1 has been designed and realised for 2D airfoil characterisation The PT 1 wake rake system consists of a main rear support a central body and a fore part together resulting in the complete long configuration By omitting the central body the short configurat
22. performed to the Virtual Instrument Communicator Task which is located on Data Acquisition Host 8 5 IMAGING CAPABILITY The test performed can also be documented by means of video and still imaging reporting Both optical and digital imaging may be recorded during or after the run Two video cameras are positioned inside the plenum looking at the model from different viewpoints The video image is displayed on the monitors in the control room Different recording formats are available Particular customer request can be discussed during the meetings before the test 8 6 MODEL SYSTEM MSS SUPPORT The Model Support Fig 12 consists of an arc sector with a sting pod that can be manually positioned at pitch angles of 0 2 47 5 and 15 Both the arc sector itself and the leading edge of the arc sector are removable to allow testing with various geometries The initial leading edge geometry is a 4 to 1 elliptical shaped nose and a 20 included angle taper The sting pod has an instrumentation passage large enough to hold up to 50 pressure tubes and pass the tube directly into the strut The pod may be connected to a sting for conventional model testing and to a 4 cm diameter centreline pipe for static pressure measurements The following Fig 13 shows the current model support system installed for a 3D test on an Unmanned Space Vehicle configuration CIRA CF 09 1144 PT1 USER MANUAL Fig 12 rear sting model su
23. pport system A new motorized model support system is going to be installed soon A pictorial view is provided in the following fig 13 This system has been entirely design by CIRA Fig 13 new motorized model support system 8 7 INTERNAL BALANCES 8 7 1 3 Component Strain Gage Balance Characteristics The 3C component balance has the following characteristics Page 9 of 15 ha name moment The 3C balance has been designed and built in order to guarantee on each component a measurement accuracy of 0 1 of the relevant above listed full scale values An overload capacity of 2 times load capacity has been provided The 3C balance has been used in several test Campaign 8 7 2 6 Component Strain Gage Balance Characteristics The 6C component balance has the following characteristics moment moment moment The 6C balance is designed in order to guarantee each component measurement accuracy of 0 1 of the relevant above listed full scale values The balance has overload capacity of 2 times the load capacity The following Fig 14 shows the internal balance acquisition unit which has been designed and built at CIRA CIRA CF 09 1144 PT1 USER MANUAL Fig 14 Internal balances acquisition unit 9 0 AUXILIARY SYSTEMS The auxiliary systems for PT 1 include the air supply system circuit exhaust system and plenum exhaust system described in the following subs
24. re B Technical Specification for Design and Realisation of CIRA USV FTB1 3D Scaled Models and the Related Test Equipments For Tests in CIRA PT 1 Transonic Wind Tunnel CIRA TS 02 108 Page 15 of 15
25. s for flow visualization tests Up to the 3 of the injected mass flow is removed through plenum exhaust system whereas the remaining 97 Is removed through a circuit exhaust system In this way it is possible both to control the speed at high Mach numbers M gt 0 8 and to achieve the desired flow qualities in the test section In the Mach number range between 0 4 and 0 8 the test section speed is controlled via the 2 throat located downstream the test section Furthermore Mach trim flaps allow performing a fine control of the Mach number The 27 throat and a set of acoustic baffles allow reducing the noise level in test section Finally the facility is equipped with two data acquisition systems dedicated to the control of the facility parameters and to the acquisition of pressures temperatures and other analog signals Fig 3 PT 1 Control room The WT circuit is located in a building that hosts the operating team and users offices and the facility control system room Fig 3 CIRA CF 09 1144 PT1 USER MANUAL The control room equipment includes the video camera monitors operator console and the engineering and data acquisition hosts which provide complete information about the test and model conditions A dedicated area is available for model preparation 4 0 TUNNEL OPERATION The maximum speed achievable in the IWI depends upon the selected configuration The maximum stagnation pressure at which the tu
26. trol is used for second throat side walls and Mach trim flaps Speed and blade pitch control is used for fan control Tunnel fill control is used to pressurize the tunnel before running Tunnel vent control is used to reduce the tunnel pressure 10 2 DATA ACQUISITION ELABORATION SYSTEM The PT 1 Data Acquisition System DAS is fully dedicated to the Test Article measurements DAS gets data related to the specific test to be performed in the wind tunnel data will come either from the model in the test section or from the tunnel itself For 2D testing a modular integrated hardware has been designed and built Three measurement systems and a turn table controller for the test article model attitude positioning have been integrated Each of these devices is controlled by a software module running on a PC called controller that operates both as Subsystem supervisors and data servers Another software module called integrator running on a remote PC is connected to each server PC through a LAN link and works as client of the different Servers The integrator centralizes respect to the operator the CIRA CF 09 1144 PT1 USER MANUAL operations oof test device configuration on line pressure transducers calibration data acquisition recording and visualization Furthermore the integrator coordinates the entire process of model attitude positioning and data recording on event for Pitch amp Pause or Pitch
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