XFOIL Version 6.96 Calculated polar for: NACA 4424 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.7845 0.10390 0.09806 -0.0817 1.0000 0.0813 -19.000 -0.7888 0.10114 0.09531 -0.0821 1.0000 0.0822 -18.750 -0.7947 0.09817 0.09235 -0.0825 1.0000 0.0831 -18.500 -0.8083 0.09413 0.08825 -0.0834 1.0000 0.0842 -18.250 -0.8169 0.08853 0.08253 -0.0875 0.9988 0.0857 -18.000 -0.8267 0.08282 0.07666 -0.0917 0.9971 0.0871 -17.750 -0.8335 0.07766 0.07134 -0.0956 0.9951 0.0886 -17.500 -0.8242 0.07484 0.06853 -0.0982 0.9931 0.0896 -17.250 -0.8206 0.07132 0.06496 -0.1012 0.9912 0.0909 -17.000 -0.8202 0.06760 0.06115 -0.1038 0.9886 0.0924 -16.750 -0.8208 0.06372 0.05715 -0.1067 0.9858 0.0940 -16.500 -0.8209 0.05988 0.05315 -0.1098 0.9831 0.0957 -16.250 -0.8104 0.05740 0.05067 -0.1121 0.9809 0.0969 -16.000 -0.8017 0.05457 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-0.0563 0.6059 0.3282 -1.750 0.1024 0.01582 0.00684 -0.0545 0.5993 0.3372 -1.500 0.1202 0.01580 0.00681 -0.0524 0.5933 0.3454 -1.250 0.1334 0.01578 0.00684 -0.0494 0.5863 0.3544 -1.000 0.1512 0.01580 0.00682 -0.0473 0.5796 0.3643 -0.750 0.1709 0.01576 0.00678 -0.0456 0.5740 0.3744 -0.500 0.1844 0.01579 0.00685 -0.0427 0.5679 0.3851 -0.250 0.1997 0.01579 0.00689 -0.0402 0.5616 0.3960 0.000 0.2181 0.01580 0.00689 -0.0383 0.5558 0.4088 0.250 0.2359 0.01580 0.00692 -0.0362 0.5505 0.4220 0.500 0.2499 0.01584 0.00702 -0.0335 0.5447 0.4364 0.750 0.2649 0.01585 0.00709 -0.0310 0.5389 0.4523 1.000 0.2828 0.01586 0.00712 -0.0289 0.5335 0.4706 1.250 0.2998 0.01589 0.00721 -0.0268 0.5286 0.4910 1.500 0.3130 0.01593 0.00736 -0.0239 0.5231 0.5133 1.750 0.3280 0.01597 0.00748 -0.0214 0.5179 0.5368 2.000 0.3451 0.01600 0.00756 -0.0193 0.5127 0.5624 2.250 0.3631 0.01605 0.00767 -0.0173 0.5081 0.5878 2.500 0.3763 0.01612 0.00788 -0.0145 0.5030 0.6127 2.750 0.3917 0.01619 0.00805 -0.0122 0.4977 0.6394 3.000 0.4099 0.01625 0.00818 -0.0103 0.4927 0.6677 3.250 0.4326 0.01630 0.00829 -0.0093 0.4881 0.6971 3.500 0.4502 0.01642 0.00859 -0.0075 0.4828 0.7289 3.750 0.4801 0.01653 0.00887 -0.0082 0.4774 0.7682 4.000 0.5303 0.01670 0.00916 -0.0129 0.4716 0.8135 4.250 0.6053 0.01704 0.00958 -0.0229 0.4655 0.8548 4.500 0.6762 0.01749 0.01012 -0.0321 0.4579 0.8831 4.750 0.7356 0.01793 0.01055 -0.0388 0.4514 0.9036 5.000 0.7822 0.01836 0.01095 -0.0429 0.4459 0.9196 5.250 0.8171 0.01881 0.01144 -0.0448 0.4396 0.9368 5.500 0.8450 0.01924 0.01185 -0.0452 0.4339 0.9546 5.750 0.8702 0.01967 0.01221 -0.0452 0.4287 0.9728 6.000 0.9005 0.02017 0.01273 -0.0464 0.4229 0.9848 6.250 0.9346 0.02074 0.01330 -0.0483 0.4166 0.9944 6.500 0.9742 0.02124 0.01373 -0.0514 0.4105 1.0000 6.750 0.9811 0.02157 0.01404 -0.0482 0.4059 1.0000 7.000 0.9880 0.02195 0.01444 -0.0450 0.4008 1.0000 7.250 0.9959 0.02235 0.01482 -0.0420 0.3956 1.0000 7.500 1.0051 0.02277 0.01516 -0.0393 0.3906 1.0000 7.750 1.0135 0.02325 0.01566 -0.0366 0.3852 1.0000 8.000 1.0223 0.02376 0.01618 -0.0339 0.3799 1.0000 8.250 1.0313 0.02429 0.01668 -0.0314 0.3747 1.0000 8.500 1.0417 0.02482 0.01717 -0.0291 0.3698 1.0000 8.750 1.0502 0.02545 0.01785 -0.0266 0.3644 1.0000 9.000 1.0585 0.02611 0.01849 -0.0242 0.3586 1.0000 9.250 1.0686 0.02675 0.01907 -0.0221 0.3537 1.0000 9.500 1.0768 0.02751 0.01988 -0.0199 0.3481 1.0000 9.750 1.0851 0.02830 0.02068 -0.0177 0.3424 1.0000 10.000 1.0940 0.02909 0.02143 -0.0157 0.3372 1.0000 10.250 1.1026 0.02994 0.02230 -0.0138 0.3319 1.0000 10.500 1.1094 0.03093 0.02332 -0.0117 0.3259 1.0000 10.750 1.1173 0.03187 0.02423 -0.0099 0.3203 1.0000 11.000 1.1251 0.03289 0.02526 -0.0081 0.3151 1.0000 11.250 1.1315 0.03403 0.02643 -0.0063 0.3092 1.0000 11.500 1.1378 0.03519 0.02757 -0.0046 0.3035 1.0000 11.750 1.1444 0.03640 0.02879 -0.0030 0.2979 1.0000 12.000 1.1498 0.03775 0.03018 -0.0014 0.2920 1.0000 12.250 1.1556 0.03907 0.03147 0.0001 0.2865 1.0000 12.500 1.1611 0.04049 0.03292 0.0015 0.2810 1.0000 12.750 1.1656 0.04203 0.03449 0.0028 0.2751 1.0000 13.000 1.1697 0.04359 0.03602 0.0041 0.2695 1.0000 13.250 1.1742 0.04524 0.03772 0.0053 0.2640 1.0000 13.500 1.1766 0.04708 0.03958 0.0064 0.2580 1.0000 13.750 1.1815 0.04869 0.04115 0.0075 0.2531 1.0000 14.000 1.1840 0.05065 0.04318 0.0084 0.2476 1.0000 14.250 1.1866 0.05260 0.04515 0.0093 0.2420 1.0000 14.500 1.1896 0.05451 0.04703 0.0102 0.2372 1.0000 14.750 1.1913 0.05667 0.04927 0.0109 0.2316 1.0000 15.000 1.1925 0.05886 0.05147 0.0115 0.2265 1.0000 15.250 1.1950 0.06092 0.05353 0.0121 0.2217 1.0000 15.500 1.1956 0.06331 0.05598 0.0126 0.2165 1.0000 15.750 1.1968 0.06559 0.05827 0.0131 0.2117 1.0000 16.000 1.1989 0.06782 0.06050 0.0135 0.2075 1.0000 16.250 1.1983 0.07042 0.06318 0.0137 0.2023 1.0000 16.500 1.1991 0.07285 0.06562 0.0140 0.1979 1.0000 16.750 1.2012 0.07514 0.06791 0.0142 0.1940 1.0000 17.000 1.1995 0.07799 0.07084 0.0142 0.1892 1.0000 17.250 1.1998 0.08055 0.07341 0.0143 0.1848 1.0000 17.500 1.2005 0.08309 0.07595 0.0143 0.1809 1.0000 17.750 1.1983 0.08606 0.07901 0.0142 0.1764 1.0000 18.000 1.1981 0.08876 0.08172 0.0140 0.1723 1.0000 18.250 1.1986 0.09138 0.08434 0.0138 0.1686 1.0000 18.500 1.1964 0.09445 0.08750 0.0135 0.1644 1.0000 18.750 1.1945 0.09744 0.09051 0.0131 0.1605 1.0000 19.000 1.1969 0.09985 0.09290 0.0128 0.1572 1.0000