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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9929 0.08162 0.07687 -0.0903 1.0000 0.0764 -19.500 -0.9996 0.07886 0.07410 -0.0904 1.0000 0.0772 -19.250 -1.0070 0.07609 0.07130 -0.0904 1.0000 0.0780 -19.000 -1.0165 0.07300 0.06816 -0.0907 1.0000 0.0789 -18.750 -1.0104 0.06937 0.06444 -0.0942 0.9987 0.0801 -18.500 -1.0056 0.06575 0.06070 -0.0975 0.9970 0.0810 -18.250 -0.9977 0.06277 0.05769 -0.1003 0.9953 0.0824 -18.000 -0.9887 0.05995 0.05487 -0.1031 0.9936 0.0835 -17.750 -0.9801 0.05694 0.05181 -0.1062 0.9923 0.0848 -17.500 -0.9727 0.05409 0.04889 -0.1085 0.9901 0.0859 -17.250 -0.9658 0.05124 0.04596 -0.1107 0.9873 0.0872 -17.000 -0.9568 0.04853 0.04312 -0.1132 0.9849 0.0883 -16.750 -0.9475 0.04603 0.04066 -0.1154 0.9829 0.0900 -16.500 -0.9342 0.04368 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2.750 0.4106 0.01181 0.00565 -0.0138 0.4948 0.6586 3.000 0.4316 0.01188 0.00577 -0.0125 0.4896 0.6888 3.250 0.4500 0.01191 0.00595 -0.0107 0.4852 0.7207 3.500 0.4701 0.01194 0.00612 -0.0093 0.4801 0.7547 3.750 0.4979 0.01198 0.00631 -0.0095 0.4748 0.7971 4.000 0.5462 0.01209 0.00651 -0.0139 0.4685 0.8434 4.250 0.6278 0.01228 0.00687 -0.0255 0.4624 0.8861 4.500 0.7063 0.01264 0.00728 -0.0363 0.4554 0.9110 4.750 0.7668 0.01313 0.00771 -0.0433 0.4486 0.9279 5.000 0.8070 0.01353 0.00813 -0.0460 0.4433 0.9428 5.250 0.8332 0.01391 0.00852 -0.0460 0.4377 0.9606 5.500 0.8642 0.01434 0.00890 -0.0470 0.4323 0.9729 5.750 0.8986 0.01478 0.00928 -0.0487 0.4266 0.9805 6.000 0.9355 0.01514 0.00967 -0.0510 0.4209 0.9865 6.250 0.9711 0.01560 0.01009 -0.0531 0.4146 0.9920 6.500 1.0099 0.01601 0.01042 -0.0560 0.4084 0.9963 6.750 1.0494 0.01631 0.01077 -0.0589 0.4029 0.9995 7.000 1.0625 0.01661 0.01105 -0.0568 0.3975 1.0000 7.250 1.0695 0.01695 0.01134 -0.0535 0.3925 1.0000 7.500 1.0786 0.01731 0.01168 -0.0506 0.3874 1.0000 7.750 1.0894 0.01765 0.01203 -0.0480 0.3825 1.0000 8.000 1.0998 0.01804 0.01241 -0.0454 0.3773 1.0000 8.250 1.1089 0.01854 0.01285 -0.0426 0.3721 1.0000 8.500 1.1209 0.01896 0.01330 -0.0404 0.3673 1.0000 8.750 1.1326 0.01942 0.01376 -0.0381 0.3616 1.0000 9.000 1.1423 0.01999 0.01430 -0.0357 0.3563 1.0000 9.250 1.1524 0.02058 0.01488 -0.0334 0.3508 1.0000 9.500 1.1650 0.02111 0.01542 -0.0315 0.3453 1.0000 9.750 1.1735 0.02182 0.01611 -0.0291 0.3393 1.0000 10.000 1.1832 0.02253 0.01680 -0.0269 0.3338 1.0000 10.250 1.1957 0.02315 0.01745 -0.0252 0.3284 1.0000 10.500 1.2042 0.02398 0.01825 -0.0231 0.3225 1.0000 10.750 1.2128 0.02483 0.01908 -0.0210 0.3169 1.0000 11.000 1.2242 0.02560 0.01989 -0.0194 0.3114 1.0000 11.250 1.2321 0.02657 0.02084 -0.0174 0.3052 1.0000 11.500 1.2396 0.02760 0.02185 -0.0155 0.2998 1.0000 11.750 1.2503 0.02851 0.02279 -0.0141 0.2940 1.0000 12.000 1.2565 0.02969 0.02395 -0.0122 0.2878 1.0000 12.250 1.2639 0.03085 0.02511 -0.0106 0.2823 1.0000 12.500 1.2730 0.03194 0.02623 -0.0092 0.2764 1.0000 12.750 1.2770 0.03339 0.02764 -0.0074 0.2705 1.0000 13.000 1.2852 0.03460 0.02888 -0.0061 0.2652 1.0000 13.250 1.2913 0.03601 0.03031 -0.0048 0.2593 1.0000 13.500 1.2940 0.03766 0.03192 -0.0032 0.2536 1.0000 13.750 1.3018 0.03902 0.03333 -0.0021 0.2487 1.0000 14.000 1.3068 0.04060 0.03491 -0.0009 0.2428 1.0000 14.250 1.3070 0.04256 0.03685 0.0005 0.2375 1.0000 14.500 1.3153 0.04398 0.03833 0.0013 0.2326 1.0000 14.750 1.3172 0.04593 0.04028 0.0024 0.2272 1.0000 15.000 1.3186 0.04790 0.04223 0.0035 0.2224 1.0000 15.250 1.3238 0.04966 0.04405 0.0042 0.2176 1.0000 15.500 1.3249 0.05177 0.04615 0.0051 0.2123 1.0000 15.750 1.3248 0.05402 0.04840 0.0060 0.2077 1.0000 16.000 1.3300 0.05585 0.05028 0.0065 0.2032 1.0000 16.250 1.3286 0.05830 0.05274 0.0072 0.1983 1.0000 16.500 1.3293 0.06055 0.05499 0.0079 0.1939 1.0000 16.750 1.3311 0.06279 0.05729 0.0083 0.1893 1.0000 17.000 1.3308 0.06522 0.05971 0.0088 0.1849 1.0000 17.250 1.3292 0.06781 0.06232 0.0092 0.1808 1.0000 17.500 1.3320 0.07003 0.06458 0.0094 0.1766 1.0000 17.750 1.3288 0.07284 0.06740 0.0097 0.1723 1.0000 18.000 1.3280 0.07540 0.06997 0.0099 0.1684 1.0000 18.250 1.3289 0.07789 0.07252 0.0100 0.1643 1.0000 18.500 1.3270 0.08066 0.07529 0.0100 0.1605 1.0000 18.750 1.3253 0.08339 0.07802 0.0101 0.1569 1.0000 19.000 1.3251 0.08607 0.08078 0.0100 0.1530 1.0000 19.250 1.3232 0.08888 0.08359 0.0098 0.1492 1.0000