XFOIL Version 6.96 Calculated polar for: NACA 2424 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1479 0.07195 0.06756 -0.0772 1.0000 0.0728 -19.500 -1.1504 0.06925 0.06479 -0.0775 1.0000 0.0736 -19.250 -1.1664 0.06510 0.06058 -0.0781 1.0000 0.0748 -19.000 -1.1793 0.06137 0.05680 -0.0785 1.0000 0.0759 -18.750 -1.1887 0.05811 0.05349 -0.0786 1.0000 0.0768 -18.500 -1.1949 0.05531 0.05064 -0.0784 1.0000 0.0779 -18.250 -1.2004 0.05266 0.04793 -0.0781 1.0000 0.0789 -18.000 -1.2033 0.05034 0.04555 -0.0776 1.0000 0.0798 -17.750 -1.2095 0.04784 0.04299 -0.0769 1.0000 0.0805 -17.500 -1.2204 0.04508 0.04018 -0.0759 1.0000 0.0816 -17.250 -1.2136 0.04247 0.03755 -0.0776 0.9991 0.0833 -17.000 -1.2010 0.04021 0.03525 -0.0795 0.9978 0.0846 -16.750 -1.1850 0.03835 0.03333 -0.0814 0.9962 0.0862 -16.500 -1.1691 0.03656 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0.5764 2.750 0.2635 0.00934 0.00375 0.0144 0.4407 0.5912 3.000 0.2825 0.00939 0.00384 0.0162 0.4345 0.6082 3.250 0.2995 0.00948 0.00395 0.0184 0.4277 0.6238 3.500 0.3212 0.00953 0.00404 0.0196 0.4224 0.6393 3.750 0.3418 0.00958 0.00415 0.0210 0.4162 0.6572 4.000 0.3599 0.00968 0.00429 0.0228 0.4093 0.6756 4.250 0.3813 0.00977 0.00442 0.0240 0.4034 0.6926 4.500 0.4046 0.00984 0.00454 0.0248 0.3976 0.7119 4.750 0.4266 0.00994 0.00470 0.0258 0.3908 0.7335 5.000 0.4499 0.01005 0.00487 0.0265 0.3843 0.7558 5.250 0.4798 0.01011 0.00503 0.0259 0.3783 0.7803 5.500 0.5093 0.01026 0.00523 0.0252 0.3708 0.8056 5.750 0.5392 0.01039 0.00543 0.0245 0.3640 0.8307 6.000 0.5713 0.01050 0.00562 0.0233 0.3576 0.8555 6.250 0.6042 0.01072 0.00587 0.0218 0.3495 0.8802 6.500 0.6492 0.01089 0.00612 0.0180 0.3428 0.9026 6.750 0.7019 0.01123 0.00647 0.0124 0.3337 0.9195 7.000 0.7513 0.01163 0.00686 0.0076 0.3258 0.9304 7.250 0.7948 0.01206 0.00727 0.0039 0.3173 0.9378 7.500 0.8244 0.01256 0.00773 0.0031 0.3097 0.9485 7.750 0.8426 0.01296 0.00813 0.0047 0.3037 0.9621 8.000 0.8723 0.01348 0.00860 0.0036 0.2955 0.9669 8.250 0.8979 0.01393 0.00903 0.0036 0.2886 0.9739 8.500 0.9232 0.01443 0.00950 0.0034 0.2816 0.9786 8.750 0.9552 0.01495 0.00998 0.0018 0.2740 0.9808 9.000 0.9872 0.01542 0.01043 0.0002 0.2668 0.9836 9.250 1.0156 0.01604 0.01100 -0.0009 0.2590 0.9869 9.500 1.0438 0.01655 0.01150 -0.0017 0.2526 0.9901 9.750 1.0711 0.01721 0.01211 -0.0027 0.2450 0.9923 10.000 1.1033 0.01767 0.01256 -0.0045 0.2388 0.9943 10.250 1.1323 0.01824 0.01310 -0.0059 0.2321 0.9965 10.500 1.1612 0.01883 0.01366 -0.0073 0.2257 0.9984 10.750 1.1904 0.01945 0.01426 -0.0088 0.2195 0.9999 11.250 1.2045 0.02075 0.01555 -0.0035 0.2099 1.0000 11.500 1.2113 0.02147 0.01625 -0.0010 0.2051 1.0000 11.750 1.2161 0.02234 0.01711 0.0017 0.2002 1.0000 12.000 1.2252 0.02307 0.01785 0.0038 0.1964 1.0000 12.250 1.2338 0.02387 0.01865 0.0058 0.1920 1.0000 12.500 1.2377 0.02497 0.01973 0.0082 0.1870 1.0000 12.750 1.2470 0.02582 0.02060 0.0100 0.1835 1.0000 13.000 1.2545 0.02681 0.02160 0.0119 0.1794 1.0000 13.250 1.2601 0.02796 0.02274 0.0138 0.1753 1.0000 13.500 1.2658 0.02917 0.02395 0.0156 0.1715 1.0000 13.750 1.2752 0.03017 0.02498 0.0170 0.1681 1.0000 14.000 1.2798 0.03154 0.02635 0.0186 0.1642 1.0000 14.250 1.2833 0.03303 0.02784 0.0202 0.1599 1.0000 14.500 1.2915 0.03424 0.02908 0.0214 0.1569 1.0000 14.750 1.2959 0.03576 0.03060 0.0228 0.1527 1.0000 15.000 1.2966 0.03762 0.03245 0.0242 0.1485 1.0000 15.250 1.3042 0.03898 0.03386 0.0251 0.1457 1.0000 15.500 1.3073 0.04073 0.03561 0.0262 0.1413 1.0000 15.750 1.3060 0.04289 0.03777 0.0274 0.1375 1.0000 16.000 1.3127 0.04441 0.03932 0.0282 0.1342 1.0000 16.250 1.3140 0.04645 0.04138 0.0290 0.1311 1.0000 16.500 1.3126 0.04875 0.04369 0.0299 0.1278 1.0000 16.750 1.3160 0.05067 0.04564 0.0305 0.1248 1.0000 17.000 1.3184 0.05269 0.04769 0.0311 0.1225 1.0000 17.250 1.3158 0.05522 0.05024 0.0316 0.1195 1.0000 17.500 1.3144 0.05769 0.05275 0.0321 0.1167 1.0000 17.750 1.3171 0.05979 0.05488 0.0325 0.1145 1.0000 18.000 1.3146 0.06242 0.05754 0.0328 0.1117 1.0000 18.250 1.3106 0.06522 0.06036 0.0331 0.1093 1.0000 18.500 1.3098 0.06777 0.06296 0.0332 0.1075 1.0000 18.750 1.3111 0.07012 0.06535 0.0333 0.1053 1.0000 19.000 1.3073 0.07304 0.06831 0.0333 0.1032 1.0000 19.250 1.3028 0.07604 0.07133 0.0333 0.1011 1.0000