D.7 DesCam User's Manual This program provides the camber line
Contents
1. z 0 the shape is rotated down by the value of the de sign angle of attack The result is given in the column listed as z z0 c which is now a pure camber surface with the camber at both the leading and trailing edges equal to zero The equa tions are given in Section 6 11 of the text In particular see Eq 6 109 for the details of the ro tation Friday November 17 19952. mber 17 1995 D 62 Applied Computational Aerodynamics i x c z c dz dx z z0 c 0 0 00000 0 05961 1 07277 0 000000 i 0 00274 0 06192 0 61767 0 002478 2 0 01093 0 06636 0 46497 0 007398 3 0 02447 0 07203 0 37212 0 013875 4 0 04323 0 07837 0 30444 0 021338 5 0 06699 0 08496 0 25031 0 029344 6 0 09549 0 09144 0 20439 0 037524 7 0 12843 0 09750 0 16374 0 045550 8 0 16543 0 10287 0 12646 0 053125 9 0 20611 0 10730 0 09118 0 059976 10 0 25000 0 11054 0 05671 0 065838 11 0 29663 0 11237 0 02174 0 070447 12 0 34549 04L 1252 0 01581 0 073504 13 0 39604 0 11052 0 06321 0 074520 14 0 44774 0 10600 0 11174 0 073080 15 0 50000 0 09932 0 14406 0 069511 16 0 55226 0 09115 0 16858 0 064456 17 0 60396 0 08195 0 18725 0 058341 18 0 65451 0 07213 0 20102 0 051540 19 0 70337 0 06208 0 21052 0 044399 20 0 75000 0 05213 0 21624 0 037228 21 0 79389 0 04259 0 21864 0 030300 22 0 83457 0 03370 0 21813 0 023843 23 0 87157 0 02569 0 2151 5 0 018032 24 0 90451 0 01868 0 21016 0 012991 25 0 93301 0 01279 0 20365 0 008792 26 0 95677 0 00804 0 19616 0 005459 27 0 97553 0 00443 0 18831 0 002972 28 0 98907 0 00193 0 18084 0 001279 29 0 99726 0 00047 0 17476 0 000311 30 1 00000 0 00000 0 17179 0 000000 STOP Note The data in the z c column is the surface shape including both angle of attack and camber This means that the surface starts at positive normally value of z To obtain a traditional camber line distribution that starts and stops at
3. report typos and errors to W H Mason Appendix D Programs D 61 D 7 DesCam User s Manual This program provides the camber line required to obtain the user input chord loading distribu tion for two dimensional incompressible flow using thin airfoil theory Lan s quasi vortex lattice method is used The program prompts the user for the name of the data set defining the chord load of interest The user is also prompted to enter the number of points at which a solution is required Fifty is enough for an extremely accurate answer The maximum is 121 INPUT DESCRIPTION all numeric input is in 2F10 5 format Card Field Variable Description 1 1 Title Up to 80 characters describing the data set case A79 2 1 FNQ number of x c ACp pairs describing design chord load the maximum is 101 3 1 XQ the x c input station for a given chord load 2 DC the design chord load at this x c ek kkk kkk kk CARD 3 is repeated FNQ times 7 7 2 2 2 2 2 2 2 2k ak Sample input NACA 6 series a 4 mean line loading 3 0 0 0 1 42857 0 4 1 42857 1 0 0 00000 Sample output enter name of input data file descam inp camber line design using quasi vortex lattice method case title NACA 6 series a 4 mean line loading design chord load n x c Delta Cp 1 0 00000 1 4286 2 0 40000 1 4286 3 1 00000 0 0000 CL 1 0000 Cm 0 0357 nter the number of points to be computed 30 Design angle of attack 3 4113 degrees Friday Nove
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