1 INPUT DATA 1. TEAM REVCON A-7D: WING and fuselage 2. 3. 1. 1.0000 247.9 0. 3. 3.0 4. 0.0 0.0 0.0 1.0 5. -2.21 -2.5 0.0 1.0 6. -14.5 -2.5 0.0 1.0 7. -14.5 0.0 0.0 1.0 8. 5.0 9. -14.5 0.0 0.0 1.0 10. -14.5 -2.5 0.0 1.0 11. -31.89 -28.18 0.0 1.0 12. -33.57 -28.18 0.0 1.0 13. -22.26 -2.5 0.0 1.0 14. -22.26 0.0 0.0 1.0 15. 3.0 16. -22.26 0.0 0.0 1.0 17. -22.26 -2.5 0.0 1.0 18. -43.17 -2.5 0.0 1.0 19. -43.17 0.0 0.0 1.0 20. BASIC LINEAR AERO 15. 20. 0.85 0.55 21. 22. 1 GEOMETRY DATA FIRST REFERENCE PLANFORM HAS 3 CURVES ROOT CHORD HEIGHT = 0.00000 VARIABLE SWEEP PIVOT POSITION X(S) = 0.00000 Y(S) = 0.00000 BREAK POINTS FOR THE REFERENCE PLANFORM POINT X Y SWEEP DIHEDRAL MOVE REF REF ANGLE ANGLE CODE 1 0.00000 0.00000 41.47668 0.00000 1 2 -2.21000 -2.50000 90.00000 0.00000 1 3 -14.50000 -2.50000 0.00000 0.00000 1 4 -14.50000 0.00000 SECOND REFERENCE PLANFORM HAS 5 CURVES ROOT CHORD HEIGHT = 0.00000 VARIABLE SWEEP PIVOT POSITION X(S) = 0.00000 Y(S) = 0.00000 BREAK POINTS FOR THE REFERENCE PLANFORM POINT X Y SWEEP DIHEDRAL MOVE REF REF ANGLE ANGLE CODE 1 -14.50000 0.00000 0.00000 0.00000 1 2 -14.50000 -2.50000 34.10509 0.00000 1 3 -31.89000 -28.18000 90.00000 0.00000 1 4 -33.57000 -28.18000 23.76968 0.00000 1 5 -22.26000 -2.50000 0.00000 0.00000 1 6 -22.26000 0.00000 THIRD REFERENCE PLANFORM HAS 3 CURVES ROOT CHORD HEIGHT = 0.00000 VARIABLE SWEEP PIVOT POSITION X(S) = 0.00000 Y(S) = 0.00000 BREAK POINTS FOR THE REFERENCE PLANFORM POINT X Y SWEEP DIHEDRAL MOVE REF REF ANGLE ANGLE CODE 1 -22.26000 0.00000 0.00000 0.00000 1 2 -22.26000 -2.50000 90.00000 0.00000 1 3 -43.17000 -2.50000 0.00000 0.00000 1 4 -43.17000 0.00000 CONFIGURATION:BASIC LINEAR AERO SCW = 15.00 VIC = 20.00 MACH = 0.85 CLDES = 0.50 SA(I), I=1,4 = 0.05 0.00 0.00 0.00 TWIST(J), J=1,4 = 0.00 0.00 0.00 0.00 PTEST = 0.00 QTEST = 0.00 ATPCOD = 0.00 OPTREP = 0.00 IOPTR0(J),J=1,4 = 0 0 0 0 1 GEOMETRY DATA CONFIGURATION : BASIC LINEAR AERO BREAK POINTS FOR THIS CONFIGURATION POINT X Y Z SWEEP DIHEDRAL MOVE ANGLE ANGLE CODE FIRST PLANFORM BREAK POINTS 1 0.00000 0.00000 0.00000 41.47668 0.00000 1 2 -2.21000 -2.50000 0.00000 90.00000 0.00000 1 3 -14.50000 -2.50000 0.00000 0.00000 0.00000 1 4 -14.50000 0.00000 0.00000 SECOND PLANFORM BREAK POINTS 1 -14.50000 0.00000 0.00000 0.00000 0.00000 1 2 -14.50000 -2.50000 0.00000 34.10509 0.00000 1 3 -31.89000 -28.18000 0.00000 90.00000 0.00000 1 4 -33.57000 -28.18000 0.00000 23.76968 0.00000 1 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-0.54550 0.00000 0.54550 0.00000 0.00000 0.00000 0.00150 REF. CHORD C AVERAGE TRUE AREA REFERENCE AREA B/2 REF. AR TRUE AR MACH NUMBER 1.00000 8.03308 452.74417 247.89999 28.18000 12.81343 7.01599 0.85000 1 COMPLETE CONFIGURATION WING-BODY CHARACTERISTICS LIFT INDUCED DRAG (FAR FIELD SOLUTION) DESIRED CL COMPUTED ALPHA CL(WB) CDI AT CL(WB) CDI/(CL(WB)**2) (1/PI*AR REF) = 0.02484) 0.50000 3.70300 0.47358 0.00630 0.02809 COMPLETE CONFIGURATION CHARACTERISTICS CL ALPHA CL(TWIST) ALPHA AT CL=0 Y CP CM/CL CMO PER RADIAN PER DEGREE 7.73639 0.13503 0.00000 0.00000 -0.42455 -22.24648 0.00000 FIRST PLANFORM 0.29931 0.00522 0.00000 0.00000 -0.04224 SECOND PLANFORM 7.32752 0.12789 0.00000 0.00000 -0.44588 THIRD PLANFORM 0.10955 0.00191 0.00000 0.00000 -0.04243 ADDITIONAL LOADING WITH CL BASED ON S(TRUE) -AT CL DES- LOAD DUE ADD. LOAD AT BASIC LOAD SPAN LOAD AT X LOCATION OF STATION 2Y/B SL COEF CL RATIO C RATIO TO TWIST CL= 0.00000 AT CL=0 DESIRED CL LOCAL CENT PR FIRST PLANFORM SPAN LOAD DISTRIBUTION 1 -0.06372 0.39913 0.24830 1.60745 0.00000 0.00000 0.00000 0.10927 -5.54619 2 -0.01936 0.48385 0.27728 1.74501 0.00000 0.00000 0.00000 0.13247 -4.92565 SECOND PLANFORM SPAN LOAD DISTRIBUTION 3 -0.97500 0.40026 1.74105 0.22989 0.00000 0.00000 0.00000 0.10958 -31.79449 4 -0.92500 0.54738 2.01666 0.27143 0.00000 0.00000 0.00000 0.14986 -30.98035 5 -0.87500 0.64069 2.04723 0.31296 0.00000 0.00000 0.00000 0.17541 -30.12927 6 -0.82500 0.71568 2.01895 0.35448 0.00000 0.00000 0.00000 0.19594 -29.26688 7 -0.77500 0.78185 1.97431 0.39601 0.00000 0.00000 0.00000 0.21405 -28.40084 8 -0.72500 0.84220 1.92487 0.43754 0.00000 0.00000 0.00000 0.23057 -27.53354 9 -0.67500 0.89789 1.87426 0.47906 0.00000 0.00000 0.00000 0.24582 -26.66588 10 -0.62500 0.94939 1.82368 0.52059 0.00000 0.00000 0.00000 0.25992 -25.79834 11 -0.57500 0.99690 1.77347 0.56212 0.00000 0.00000 0.00000 0.27293 -24.93129 12 -0.52500 1.04048 1.72365 0.60365 0.00000 0.00000 0.00000 0.28486 -24.06513 13 -0.47500 1.08008 1.67409 0.64518 0.00000 0.00000 0.00000 0.29570 -23.20043 14 -0.42500 1.11563 1.62462 0.68670 0.00000 0.00000 0.00000 0.30543 -22.33807 15 -0.37500 1.14699 1.57503 0.72823 0.00000 0.00000 0.00000 0.31402 -21.47948 16 -0.32500 1.17400 1.52515 0.76976 0.00000 0.00000 0.00000 0.32141 -20.62699 17 -0.27500 1.19649 1.47480 0.81129 0.00000 0.00000 0.00000 0.32757 -19.78419 18 -0.22500 1.21436 1.42395 0.85281 0.00000 0.00000 0.00000 0.33246 -18.95662 19 -0.17500 1.22777 1.37282 0.89434 0.00000 0.00000 0.00000 0.33613 -18.15248 20 -0.11936 1.23820 1.31645 0.94056 0.00000 0.00000 0.00000 0.33899 -17.28864 21 -0.06372 0.85393 0.88398 0.96601 0.00000 0.00000 0.00000 0.23378 -17.61176 22 -0.01936 0.77925 0.80667 0.96601 0.00000 0.00000 0.00000 0.21334 -17.75796 THIRD PLANFORM SPAN LOAD DISTRIBUTION 23 -0.06372 0.14729 0.05659 2.60299 0.00000 0.00000 0.00000 0.04033 -26.12024 24 -0.01936 0.17554 0.06744 2.60299 0.00000 0.00000 0.00000 0.04806 -26.21979 INDUCED DRAG, LEADING EDGE THRUST AND SUCTION COEFFICIENT CHARACTERISTICS COMPUTED AT THE DESIRED CL FROM A NEAR FIELD SOLUTION SECTION COEFFICIENTS L. E. SWEEP STATION 2Y/B ANGLE CDII C/2B CT C/2B CS C/2B CONTRIBUTION OF THE FIRST PLANFORM TO THE CHORD OR DRAG FORCE 1 -0.06372 41.47668 0.00067 -0.00008 -0.00010 2 -0.01936 41.47668 0.00067 -0.00008 -0.00010 CONTRIBUTION OF THE SECOND PLANFORM TO THE CHORD OR DRAG FORCE 3 -0.97500 34.10510 -0.00021 0.00072 0.00086 4 -0.92500 34.10510 -0.00019 0.00088 0.00106 5 -0.87500 34.10510 -0.00017 0.00098 0.00118 6 -0.82500 34.10510 -0.00015 0.00105 0.00127 7 -0.77500 34.10510 -0.00012 0.00111 0.00134 8 -0.72500 34.10510 -0.00009 0.00116 0.00140 9 -0.67500 34.10510 -0.00006 0.00119 0.00144 10 -0.62500 34.10510 -0.00002 0.00122 0.00147 11 -0.57500 34.10510 0.00002 0.00124 0.00150 12 -0.52500 34.10510 0.00007 0.00125 0.00150 13 -0.47500 34.10510 0.00012 0.00124 0.00150 14 -0.42500 34.10510 0.00018 0.00122 0.00148 15 -0.37500 34.10510 0.00025 0.00119 0.00144 16 -0.32500 34.10510 0.00034 0.00114 0.00138 17 -0.27500 34.10510 0.00045 0.00106 0.00128 18 -0.22500 34.10510 0.00059 0.00094 0.00113 19 -0.17500 34.10510 0.00085 0.00070 0.00084 20 -0.11936 34.10510 0.00160 -0.00008 -0.00016 21 -0.06372 0.00000 -0.00082 0.00195 0.00198 22 -0.01936 0.00000 0.00238 -0.00141 -0.00141 CONTRIBUTION OF THE THIRD PLANFORM TO THE CHORD OR DRAG FORCE 23 -0.06372 0.00000 0.00047 -0.00025 -0.00025 24 -0.01936 0.00000 0.00047 -0.00025 -0.00025 TOTAL COEFFICIENTS CDII/CL**2 = 0.02741 CT= 0.02477 CS= 0.02952 1 GEOMETRY DATA 1 END OF FILE ENCOUNTERED AFTER CONFIGURATION BASIC LINEAR AERO