XFOIL Version 6.96 Calculated polar for: WORTMANN FX L V-152 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -1.1638 0.11361 0.10988 0.0201 1.0005 0.0087 -18.000 -1.1770 0.10712 0.10327 0.0169 1.0005 0.0087 -17.750 -1.1899 0.10079 0.09682 0.0138 1.0005 0.0087 -17.500 -1.2021 0.09471 0.09062 0.0109 1.0005 0.0087 -17.250 -1.2136 0.08889 0.08467 0.0083 1.0005 0.0088 -17.000 -1.2241 0.08335 0.07901 0.0059 1.0005 0.0088 -16.750 -1.2332 0.07819 0.07373 0.0037 1.0005 0.0088 -16.500 -1.2412 0.07336 0.06878 0.0018 1.0005 0.0089 -16.250 -1.2480 0.06880 0.06411 0.0001 1.0005 0.0089 -16.000 -1.2536 0.06457 0.05977 -0.0014 1.0005 0.0090 -15.750 -1.2582 0.06059 0.05568 -0.0027 1.0005 0.0091 -15.500 -1.2615 0.05694 0.05192 -0.0037 1.0005 0.0091 -15.250 -1.2641 0.05354 0.04841 -0.0045 1.0005 0.0092 -15.000 -1.2660 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0.6441 0.6121 -0.750 -0.0779 0.00904 0.00310 -0.0015 0.6403 0.6164 -0.500 -0.0489 0.00902 0.00311 -0.0017 0.6365 0.6203 -0.250 -0.0199 0.00904 0.00311 -0.0018 0.6325 0.6246 0.000 0.0090 0.00911 0.00313 -0.0020 0.6281 0.6291 0.250 0.0383 0.00910 0.00312 -0.0022 0.6237 0.6325 0.500 0.0672 0.00902 0.00309 -0.0024 0.6193 0.6363 0.750 0.0962 0.00899 0.00308 -0.0026 0.6149 0.6401 1.000 0.1251 0.00902 0.00307 -0.0027 0.6102 0.6436 1.250 0.1542 0.00899 0.00308 -0.0030 0.6054 0.6471 1.500 0.1834 0.00898 0.00306 -0.0032 0.5999 0.6504 1.750 0.2120 0.00891 0.00299 -0.0033 0.5933 0.6541 2.000 0.2407 0.00886 0.00298 -0.0034 0.5857 0.6579 2.250 0.2694 0.00881 0.00297 -0.0035 0.5780 0.6616 2.500 0.2980 0.00884 0.00296 -0.0036 0.5705 0.6653 2.750 0.3270 0.00879 0.00295 -0.0037 0.5605 0.6688 3.000 0.3554 0.00876 0.00292 -0.0038 0.5509 0.6724 3.250 0.3841 0.00869 0.00294 -0.0039 0.5393 0.6759 3.500 0.4128 0.00867 0.00295 -0.0040 0.5272 0.6795 3.750 0.4414 0.00868 0.00296 -0.0041 0.5128 0.6832 4.000 0.4696 0.00872 0.00298 -0.0042 0.4926 0.6871 4.250 0.4973 0.00881 0.00304 -0.0042 0.4739 0.6910 4.500 0.5249 0.00893 0.00316 -0.0042 0.4517 0.6950 4.750 0.5513 0.00920 0.00331 -0.0041 0.4081 0.6993 5.000 0.5753 0.00982 0.00359 -0.0038 0.3351 0.7037 5.250 0.6000 0.01036 0.00393 -0.0036 0.2893 0.7080 5.500 0.6245 0.01089 0.00428 -0.0035 0.2342 0.7126 5.750 0.6484 0.01154 0.00469 -0.0033 0.1822 0.7179 6.000 0.6735 0.01206 0.00507 -0.0032 0.1554 0.7234 6.250 0.6991 0.01239 0.00539 -0.0031 0.1364 0.7292 6.500 0.7244 0.01278 0.00572 -0.0030 0.1168 0.7360 6.750 0.7495 0.01322 0.00607 -0.0029 0.0969 0.7432 7.000 0.7738 0.01363 0.00645 -0.0026 0.0802 0.7504 7.250 0.7985 0.01404 0.00684 -0.0024 0.0695 0.7583 7.500 0.8232 0.01438 0.00723 -0.0022 0.0605 0.7665 7.750 0.8475 0.01478 0.00762 -0.0019 0.0497 0.7763 8.000 0.8708 0.01523 0.00809 -0.0016 0.0423 0.7880 8.250 0.8943 0.01564 0.00856 -0.0012 0.0379 0.8020 8.500 0.9177 0.01602 0.00901 -0.0008 0.0341 0.8188 8.750 0.9402 0.01637 0.00947 -0.0002 0.0306 0.8394 9.000 0.9612 0.01673 0.00994 0.0007 0.0280 0.8658 9.250 0.9794 0.01707 0.01041 0.0022 0.0261 0.9135 9.500 1.0092 0.01756 0.01100 0.0011 0.0246 0.9995 9.750 1.0304 0.01820 0.01164 0.0014 0.0233 0.9995 10.000 1.0511 0.01884 0.01231 0.0019 0.0220 0.9995 10.250 1.0699 0.01959 0.01310 0.0024 0.0208 0.9995 10.500 1.0871 0.02040 0.01395 0.0032 0.0198 0.9995 10.750 1.1036 0.02114 0.01476 0.0041 0.0187 0.9995 11.000 1.1169 0.02218 0.01584 0.0049 0.0177 0.9995 11.250 1.1318 0.02316 0.01689 0.0054 0.0167 0.9995 11.500 1.1468 0.02418 0.01798 0.0058 0.0155 0.9995 11.750 1.1597 0.02541 0.01926 0.0061 0.0147 0.9995 12.000 1.1742 0.02654 0.02048 0.0064 0.0136 0.9995 12.250 1.1874 0.02781 0.02181 0.0066 0.0128 0.9995 12.500 1.1996 0.02917 0.02321 0.0068 0.0122 0.9995 12.750 1.2105 0.03068 0.02479 0.0070 0.0116 0.9995 13.000 1.2212 0.03221 0.02639 0.0071 0.0111 0.9995 13.250 1.2312 0.03381 0.02804 0.0073 0.0107 0.9995 13.500 1.2403 0.03551 0.02978 0.0074 0.0103 0.9995 13.750 1.2473 0.03742 0.03174 0.0074 0.0101 0.9995 14.000 1.2519 0.03958 0.03399 0.0075 0.0099 0.9995 14.250 1.2551 0.04191 0.03641 0.0075 0.0098 0.9995 14.500 1.2571 0.04440 0.03898 0.0074 0.0097 0.9995 14.750 1.2576 0.04708 0.04175 0.0072 0.0096 0.9995 15.000 1.2568 0.04993 0.04470 0.0069 0.0095 0.9995 15.250 1.2550 0.05296 0.04783 0.0066 0.0094 0.9995 15.500 1.2524 0.05621 0.05119 0.0060 0.0093 0.9995 15.750 1.2489 0.05973 0.05481 0.0051 0.0093 0.9995 16.000 1.2443 0.06354 0.05873 0.0041 0.0092 0.9995 16.250 1.2385 0.06761 0.06291 0.0028 0.0091 0.9995 16.500 1.2316 0.07196 0.06737 0.0014 0.0091 0.9995 16.750 1.2235 0.07661 0.07213 -0.0003 0.0091 0.9995 17.000 1.2142 0.08156 0.07720 -0.0022 0.0090 0.9995 17.250 1.2038 0.08682 0.08258 -0.0043 0.0090 0.9995 17.500 1.1923 0.09237 0.08824 -0.0067 0.0090 0.9995 17.750 1.1800 0.09817 0.09417 -0.0092 0.0090 0.9995 18.000 1.1669 0.10425 0.10037 -0.0120 0.0090 0.9995 18.250 1.1535 0.11046 0.10669 -0.0149 0.0090 0.9995