XFOIL Version 6.96 Calculated polar for: USA 45 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -1.0624 0.04771 0.04485 -0.0770 1.0000 0.0095 -16.500 -1.0954 0.03933 0.03621 -0.0839 1.0000 0.0093 -16.250 -1.1086 0.03539 0.03212 -0.0855 1.0000 0.0095 -16.000 -1.1162 0.03265 0.02926 -0.0854 1.0000 0.0096 -15.750 -1.1201 0.03061 0.02710 -0.0842 1.0000 0.0097 -15.500 -1.1216 0.02898 0.02538 -0.0823 1.0000 0.0099 -15.250 -1.1210 0.02767 0.02397 -0.0799 1.0000 0.0102 -15.000 -1.1205 0.02655 0.02275 -0.0769 1.0000 0.0102 -14.750 -1.1202 0.02563 0.02174 -0.0733 1.0000 0.0104 -14.500 -1.1202 0.02481 0.02084 -0.0692 1.0000 0.0105 -14.250 -1.1144 0.02395 0.01991 -0.0661 1.0000 0.0107 -14.000 -1.1072 0.02317 0.01906 -0.0631 1.0000 0.0110 -13.750 -1.0986 0.02246 0.01830 -0.0602 1.0000 0.0113 -13.500 -1.0825 0.02175 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0.4548 0.00807 0.00205 -0.0378 0.3136 0.6819 1.500 0.4758 0.00786 0.00211 -0.0362 0.3114 0.7653 1.750 0.4967 0.00770 0.00219 -0.0345 0.3093 0.8458 2.000 0.5225 0.00766 0.00229 -0.0339 0.3068 0.8971 2.250 0.5544 0.00772 0.00239 -0.0346 0.3039 0.9276 2.500 0.5936 0.00785 0.00251 -0.0370 0.3004 0.9467 2.750 0.6295 0.00798 0.00262 -0.0387 0.2975 0.9571 3.000 0.6677 0.00810 0.00272 -0.0410 0.2952 0.9631 3.250 0.7018 0.00822 0.00282 -0.0423 0.2928 0.9715 3.500 0.7385 0.00835 0.00293 -0.0443 0.2901 0.9746 3.750 0.7716 0.00849 0.00303 -0.0454 0.2871 0.9775 4.000 0.8021 0.00864 0.00314 -0.0461 0.2839 0.9809 4.250 0.8321 0.00875 0.00325 -0.0466 0.2820 0.9841 4.500 0.8658 0.00886 0.00335 -0.0480 0.2798 0.9857 4.750 0.8987 0.00897 0.00346 -0.0492 0.2770 0.9876 5.000 0.9306 0.00911 0.00357 -0.0502 0.2737 0.9898 5.250 0.9614 0.00928 0.00371 -0.0510 0.2696 0.9922 5.500 0.9922 0.00941 0.00383 -0.0518 0.2657 0.9942 5.750 1.0248 0.00954 0.00394 -0.0530 0.2617 0.9958 6.000 1.0567 0.00969 0.00408 -0.0541 0.2578 0.9974 6.250 1.0882 0.00987 0.00423 -0.0552 0.2524 0.9989 6.500 1.1201 0.01001 0.00437 -0.0563 0.2479 1.0000 6.750 1.1407 0.01019 0.00453 -0.0550 0.2427 1.0000 7.000 1.1608 0.01036 0.00469 -0.0536 0.2386 1.0000 7.250 1.1815 0.01052 0.00485 -0.0523 0.2332 1.0000 7.500 1.2004 0.01078 0.00506 -0.0508 0.2248 1.0000 7.750 1.2201 0.01100 0.00525 -0.0494 0.2163 1.0000 8.000 1.2389 0.01127 0.00549 -0.0478 0.2082 1.0000 8.250 1.2564 0.01162 0.00577 -0.0461 0.1968 1.0000 8.500 1.2723 0.01204 0.00612 -0.0441 0.1825 1.0000 8.750 1.2842 0.01266 0.00660 -0.0415 0.1613 1.0000 9.000 1.2935 0.01339 0.00719 -0.0385 0.1387 1.0000 9.250 1.3011 0.01418 0.00785 -0.0353 0.1184 1.0000 9.500 1.3031 0.01500 0.00855 -0.0310 0.0989 1.0000 9.750 1.2860 0.01658 0.00988 -0.0240 0.0565 1.0000 10.000 1.2741 0.01821 0.01142 -0.0184 0.0190 1.0000 10.250 1.2848 0.01891 0.01213 -0.0164 0.0158 1.0000 10.500 1.2965 0.01959 0.01285 -0.0146 0.0142 1.0000 10.750 1.3080 0.02034 0.01363 -0.0129 0.0132 1.0000 11.000 1.3182 0.02121 0.01454 -0.0113 0.0122 1.0000 11.250 1.3284 0.02214 0.01552 -0.0098 0.0115 1.0000 11.500 1.3387 0.02313 0.01657 -0.0086 0.0110 1.0000 11.750 1.3477 0.02429 0.01777 -0.0074 0.0104 1.0000 12.000 1.3560 0.02558 0.01911 -0.0064 0.0101 1.0000 12.250 1.3621 0.02714 0.02073 -0.0055 0.0096 1.0000 12.500 1.3662 0.02899 0.02264 -0.0048 0.0091 1.0000 12.750 1.3717 0.03083 0.02455 -0.0044 0.0088 1.0000 13.000 1.3751 0.03300 0.02680 -0.0041 0.0086 1.0000 13.250 1.3772 0.03539 0.02926 -0.0041 0.0084 1.0000 13.500 1.3777 0.03808 0.03204 -0.0042 0.0081 1.0000 13.750 1.3763 0.04108 0.03512 -0.0046 0.0080 1.0000 14.000 1.3719 0.04451 0.03864 -0.0051 0.0078 1.0000 14.250 1.3653 0.04830 0.04253 -0.0058 0.0076 1.0000 14.500 1.3579 0.05225 0.04657 -0.0065 0.0074 1.0000 14.750 1.3471 0.05668 0.05110 -0.0075 0.0073 1.0000 15.000 1.3357 0.06126 0.05578 -0.0085 0.0072 1.0000 15.250 1.3221 0.06611 0.06073 -0.0095 0.0071 1.0000 15.500 1.3085 0.07106 0.06578 -0.0107 0.0070 1.0000 15.750 1.2963 0.07584 0.07066 -0.0119 0.0069 1.0000 16.000 1.2810 0.08114 0.07605 -0.0132 0.0068 1.0000 16.250 1.2757 0.08511 0.08009 -0.0142 0.0067 1.0000