XFOIL Version 6.96 Calculated polar for: USA 51 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.5087 0.06789 0.06644 -0.0305 1.0000 0.0120 -7.750 -0.5206 0.06308 0.06160 -0.0314 1.0000 0.0122 -7.500 -0.5620 0.03852 0.03642 -0.0391 0.9968 0.0092 -7.250 -0.5787 0.01924 0.01539 -0.0386 0.9906 0.0089 -7.000 -0.5487 0.01779 0.01369 -0.0395 0.9883 0.0095 -6.750 -0.5152 0.01700 0.01272 -0.0409 0.9864 0.0098 -6.500 -0.4876 0.01388 0.00916 -0.0416 0.9845 0.0106 -6.250 -0.4519 0.01324 0.00845 -0.0435 0.9834 0.0111 -6.000 -0.4235 0.01272 0.00788 -0.0436 0.9799 0.0117 -5.750 -0.3914 0.01213 0.00722 -0.0445 0.9767 0.0124 -5.500 -0.3561 0.01154 0.00655 -0.0461 0.9742 0.0131 -5.250 -0.3203 0.01075 0.00566 -0.0479 0.9723 0.0141 -5.000 -0.2832 0.01022 0.00513 -0.0500 0.9705 0.0157 -4.750 -0.2547 0.00991 0.00481 -0.0500 0.9652 0.0167 -4.500 -0.2237 0.00959 0.00445 -0.0506 0.9602 0.0180 -4.250 -0.1908 0.00912 0.00392 -0.0516 0.9559 0.0194 -4.000 -0.1667 0.00863 0.00341 -0.0507 0.9465 0.0215 -3.750 -0.1371 0.00843 0.00321 -0.0510 0.9373 0.0239 -3.500 -0.1085 0.00825 0.00300 -0.0509 0.9250 0.0256 -3.250 -0.0824 0.00784 0.00249 -0.0504 0.9055 0.0280 -3.000 -0.0554 0.00759 0.00212 -0.0500 0.8740 0.0313 -2.750 -0.0301 0.00752 0.00189 -0.0492 0.8355 0.0339 -2.500 -0.0054 0.00751 0.00171 -0.0484 0.8047 0.0355 -2.250 0.0191 0.00743 0.00150 -0.0475 0.7780 0.0404 -2.000 0.0432 0.00738 0.00136 -0.0465 0.7486 0.0497 -1.750 0.0663 0.00711 0.00125 -0.0456 0.7240 0.1179 -1.500 0.0897 0.00687 0.00117 -0.0447 0.7006 0.1942 -1.250 0.1131 0.00664 0.00110 -0.0438 0.6751 0.2738 -1.000 0.1346 0.00623 0.00103 -0.0427 0.6482 0.4152 -0.750 0.1546 0.00583 0.00098 -0.0412 0.6151 0.5656 -0.500 0.1735 0.00559 0.00099 -0.0393 0.5718 0.6990 -0.250 0.1927 0.00554 0.00103 -0.0374 0.5221 0.7864 0.000 0.2142 0.00557 0.00107 -0.0358 0.4846 0.8454 0.250 0.2387 0.00561 0.00112 -0.0350 0.4590 0.8859 0.500 0.2699 0.00567 0.00119 -0.0355 0.4410 0.9272 0.750 0.3227 0.00585 0.00130 -0.0410 0.4249 0.9617 1.000 0.3673 0.00603 0.00141 -0.0446 0.4119 0.9783 1.250 0.4045 0.00616 0.00148 -0.0466 0.4018 0.9850 1.500 0.4434 0.00628 0.00153 -0.0491 0.3910 0.9891 1.750 0.4820 0.00642 0.00160 -0.0514 0.3790 0.9939 2.000 0.5254 0.00652 0.00163 -0.0549 0.3666 0.9974 2.250 0.5660 0.00662 0.00166 -0.0578 0.3520 1.0000 2.500 0.5886 0.00670 0.00169 -0.0568 0.3396 1.0000 2.750 0.6113 0.00681 0.00174 -0.0558 0.3249 1.0000 3.000 0.6341 0.00694 0.00180 -0.0548 0.3080 1.0000 3.250 0.6564 0.00713 0.00189 -0.0537 0.2836 1.0000 3.500 0.6772 0.00746 0.00203 -0.0524 0.2417 1.0000 3.750 0.6922 0.00834 0.00242 -0.0501 0.1431 1.0000 4.000 0.7138 0.00866 0.00263 -0.0490 0.1246 1.0000 4.250 0.7367 0.00888 0.00281 -0.0480 0.1168 1.0000 4.500 0.7601 0.00905 0.00297 -0.0471 0.1125 1.0000 4.750 0.7832 0.00926 0.00317 -0.0462 0.1073 1.0000 5.000 0.8067 0.00945 0.00335 -0.0453 0.1033 1.0000 5.250 0.8306 0.00958 0.00349 -0.0445 0.0997 1.0000 5.500 0.8535 0.00984 0.00369 -0.0436 0.0912 1.0000 5.750 0.8757 0.01015 0.00388 -0.0426 0.0693 1.0000 6.000 0.8921 0.01102 0.00455 -0.0405 0.0220 1.0000 6.250 0.9145 0.01134 0.00492 -0.0395 0.0191 1.0000 6.500 0.9367 0.01167 0.00529 -0.0384 0.0171 1.0000 6.750 0.9575 0.01214 0.00580 -0.0371 0.0150 1.0000 7.000 0.9776 0.01268 0.00644 -0.0356 0.0137 1.0000 7.250 0.9995 0.01304 0.00684 -0.0345 0.0130 1.0000 7.500 1.0206 0.01346 0.00731 -0.0333 0.0122 1.0000 7.750 1.0416 0.01388 0.00776 -0.0321 0.0113 1.0000 8.000 1.0614 0.01440 0.00831 -0.0308 0.0106 1.0000 8.250 1.0724 0.01568 0.00975 -0.0279 0.0096 1.0000 8.500 1.0933 0.01607 0.01018 -0.0268 0.0093 1.0000 8.750 1.1122 0.01661 0.01078 -0.0253 0.0090 1.0000 9.000 1.1287 0.01733 0.01157 -0.0235 0.0087 1.0000 9.250 1.1459 0.01796 0.01226 -0.0218 0.0082 1.0000 9.500 1.1616 0.01868 0.01304 -0.0199 0.0079 1.0000 9.750 1.1769 0.01938 0.01381 -0.0181 0.0076 1.0000 10.000 1.1909 0.02014 0.01462 -0.0160 0.0073 1.0000 10.250 1.2026 0.02099 0.01552 -0.0137 0.0070 1.0000 10.500 1.2072 0.02203 0.01664 -0.0102 0.0069 1.0000 10.750 1.1941 0.02429 0.01902 -0.0044 0.0065 1.0000 11.000 1.1993 0.02552 0.02033 -0.0015 0.0064 1.0000 11.250 1.2076 0.02653 0.02143 0.0008 0.0063 1.0000 11.500 1.2186 0.02730 0.02229 0.0026 0.0060 1.0000 11.750 1.2229 0.02874 0.02383 0.0048 0.0058 1.0000 12.000 1.2256 0.03044 0.02563 0.0069 0.0057 1.0000 12.250 1.2289 0.03216 0.02746 0.0085 0.0056 1.0000 12.500 1.2270 0.03465 0.03008 0.0103 0.0056 1.0000 12.750 1.2282 0.03685 0.03240 0.0114 0.0055 1.0000 13.000 1.2301 0.03902 0.03467 0.0119 0.0053 1.0000 13.250 1.2271 0.04199 0.03778 0.0125 0.0053 1.0000 13.500 1.2277 0.04453 0.04042 0.0122 0.0051 1.0000 13.750 1.2216 0.04814 0.04419 0.0122 0.0051 1.0000 14.000 1.2116 0.05244 0.04867 0.0119 0.0052 1.0000 14.250 1.2125 0.05532 0.05161 0.0104 0.0050 1.0000 14.500 1.2001 0.06025 0.05671 0.0091 0.0050 1.0000 14.750 1.1986 0.06381 0.06034 0.0071 0.0049 1.0000 15.000 1.1895 0.06860 0.06526 0.0049 0.0049 1.0000 15.250 1.1429 0.07962 0.07667 0.0020 0.0053 1.0000 15.500 1.1480 0.08248 0.07953 -0.0005 0.0050 1.0000 15.750 1.1280 0.08980 0.08703 -0.0040 0.0050 1.0000 16.000 1.1347 0.09257 0.08977 -0.0065 0.0048 1.0000 16.250 1.1105 0.10100 0.09838 -0.0105 0.0049 1.0000 16.500 1.0546 0.11678 0.11451 -0.0185 0.0053 1.0000 16.750 1.0444 0.12347 0.12128 -0.0225 0.0052 1.0000 17.000 1.0175 0.13458 0.13254 -0.0288 0.0054 1.0000 17.250 0.9985 0.14441 0.14249 -0.0345 0.0054 1.0000 17.500 0.9735 0.15652 0.15472 -0.0414 0.0055 1.0000 17.750 0.9436 0.17115 0.16943 -0.0493 0.0058 1.0000