XFOIL Version 6.96 Calculated polar for: NACA 16-018 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0909 0.08379 0.07948 -0.0801 0.9983 0.0128 -19.500 -1.1006 0.07873 0.07427 -0.0823 0.9978 0.0130 -19.250 -1.1077 0.07419 0.06959 -0.0841 0.9973 0.0132 -19.000 -1.1129 0.07006 0.06531 -0.0856 0.9967 0.0134 -18.750 -1.1159 0.06634 0.06144 -0.0869 0.9961 0.0136 -18.500 -1.1175 0.06288 0.05784 -0.0879 0.9955 0.0139 -18.250 -1.1184 0.05954 0.05441 -0.0888 0.9950 0.0142 -18.000 -1.1160 0.05667 0.05144 -0.0896 0.9944 0.0145 -17.750 -1.1110 0.05416 0.04884 -0.0903 0.9940 0.0149 -17.500 -1.1063 0.05195 0.04654 -0.0903 0.9931 0.0153 -17.250 -1.1010 0.04990 0.04440 -0.0901 0.9920 0.0157 -17.000 -1.0943 0.04798 0.04238 -0.0899 0.9909 0.0162 -16.750 -1.0867 0.04615 0.04044 -0.0897 0.9898 0.0167 -16.500 -1.0774 0.04444 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0.00466 -0.0047 0.8713 0.8290 -1.500 -0.1421 0.00941 0.00484 -0.0042 0.8678 0.8325 -1.250 -0.1232 0.00945 0.00488 -0.0023 0.8647 0.8371 -1.000 -0.1166 0.00930 0.00468 0.0024 0.8613 0.8432 -0.750 -0.0764 0.00931 0.00469 -0.0008 0.8603 0.8445 -0.500 -0.0376 0.00931 0.00468 -0.0037 0.8593 0.8459 -0.250 0.0012 0.00931 0.00467 -0.0065 0.8583 0.8473 0.000 0.0000 0.00946 0.00485 0.0000 0.8520 0.8520 0.250 -0.0012 0.00931 0.00467 0.0065 0.8473 0.8583 0.500 0.0376 0.00931 0.00468 0.0037 0.8459 0.8593 0.750 0.0764 0.00931 0.00469 0.0008 0.8445 0.8603 1.000 0.1167 0.00930 0.00468 -0.0024 0.8432 0.8613 1.250 0.1233 0.00945 0.00488 0.0023 0.8371 0.8647 1.500 0.1422 0.00941 0.00484 0.0042 0.8325 0.8678 1.750 0.1670 0.00924 0.00466 0.0047 0.8290 0.8713 2.000 0.1715 0.00928 0.00472 0.0099 0.8219 0.8749 2.250 0.2059 0.00919 0.00463 0.0083 0.8143 0.8759 2.500 0.2252 0.00914 0.00457 0.0102 0.7989 0.8781 2.750 0.2444 0.00910 0.00448 0.0122 0.7805 0.8808 3.000 0.2482 0.00903 0.00437 0.0176 0.7651 0.8859 3.500 0.2877 0.00912 0.00442 0.0208 0.7318 0.8905 3.750 0.3088 0.00928 0.00449 0.0222 0.7018 0.8924 4.000 0.3165 0.00956 0.00459 0.0266 0.6551 0.8956 4.250 0.3038 0.00978 0.00460 0.0355 0.6087 0.9024 4.500 0.2972 0.01058 0.00506 0.0426 0.5300 0.9057 4.750 0.2924 0.01144 0.00558 0.0490 0.4500 0.9093 5.000 0.2919 0.01209 0.00595 0.0544 0.3834 0.9137 5.250 0.2948 0.01254 0.00618 0.0591 0.3325 0.9184 5.500 0.3101 0.01316 0.00659 0.0610 0.2796 0.9202 5.750 0.3258 0.01374 0.00698 0.0628 0.2311 0.9222 6.000 0.3423 0.01427 0.00734 0.0644 0.1909 0.9245 6.250 0.3585 0.01470 0.00764 0.0662 0.1611 0.9274 6.500 0.3708 0.01497 0.00784 0.0689 0.1403 0.9314 6.750 0.3888 0.01535 0.00813 0.0702 0.1209 0.9336 7.500 0.4544 0.01662 0.00925 0.0717 0.0786 0.9382 7.750 0.4747 0.01701 0.00961 0.0725 0.0688 0.9404 8.000 0.4921 0.01736 0.00994 0.0740 0.0610 0.9431 8.250 0.5036 0.01764 0.01019 0.0767 0.0548 0.9471 8.500 0.5273 0.01807 0.01064 0.0767 0.0505 0.9482 8.750 0.5500 0.01856 0.01111 0.0769 0.0467 0.9494 9.000 0.5729 0.01901 0.01158 0.0770 0.0445 0.9506 9.250 0.5947 0.01945 0.01206 0.0774 0.0425 0.9521 9.500 0.6150 0.01992 0.01254 0.0780 0.0407 0.9538 9.750 0.6328 0.02042 0.01305 0.0791 0.0389 0.9561 10.000 0.6424 0.02079 0.01344 0.0821 0.0379 0.9605 10.250 0.6657 0.02130 0.01401 0.0819 0.0369 0.9613 10.500 0.6882 0.02184 0.01460 0.0819 0.0357 0.9621 10.750 0.7100 0.02241 0.01520 0.0819 0.0345 0.9630 11.000 0.7313 0.02302 0.01583 0.0820 0.0334 0.9640 11.250 0.7508 0.02374 0.01658 0.0824 0.0322 0.9653 11.500 0.7697 0.02443 0.01732 0.0828 0.0313 0.9667 11.750 0.7885 0.02503 0.01797 0.0834 0.0306 0.9684 12.000 0.8014 0.02556 0.01856 0.0852 0.0298 0.9714 12.250 0.8175 0.02616 0.01921 0.0863 0.0289 0.9732 12.500 0.8389 0.02689 0.01999 0.0860 0.0280 0.9738 12.750 0.8593 0.02770 0.02084 0.0858 0.0272 0.9744 13.000 0.8766 0.02872 0.02188 0.0859 0.0263 0.9750 13.250 0.8966 0.02950 0.02274 0.0858 0.0256 0.9757 13.500 0.9158 0.03028 0.02360 0.0857 0.0248 0.9765 13.750 0.9335 0.03114 0.02454 0.0859 0.0240 0.9774 14.000 0.9502 0.03201 0.02547 0.0862 0.0233 0.9786 14.250 0.9661 0.03290 0.02641 0.0866 0.0225 0.9799 14.500 0.9785 0.03392 0.02747 0.0875 0.0219 0.9818 14.750 0.9870 0.03504 0.02864 0.0891 0.0213 0.9841 15.000 1.0037 0.03610 0.02981 0.0889 0.0207 0.9845 15.250 1.0193 0.03724 0.03104 0.0889 0.0200 0.9851 15.500 1.0338 0.03846 0.03235 0.0889 0.0193 0.9857 15.750 1.0477 0.03972 0.03369 0.0889 0.0187 0.9864 16.000 1.0602 0.04109 0.03512 0.0889 0.0181 0.9871 16.250 1.0714 0.04262 0.03671 0.0890 0.0176 0.9880 16.500 1.0803 0.04436 0.03853 0.0891 0.0171 0.9890 16.750 1.0895 0.04608 0.04037 0.0893 0.0167 0.9901 17.000 1.0974 0.04789 0.04228 0.0894 0.0161 0.9912 17.250 1.1041 0.04979 0.04429 0.0896 0.0157 0.9923 17.500 1.1097 0.05182 0.04641 0.0899 0.0152 0.9934 17.750 1.1150 0.05405 0.04872 0.0897 0.0148 0.9941 18.000 1.1199 0.05657 0.05134 0.0890 0.0144 0.9946 18.250 1.1222 0.05945 0.05431 0.0882 0.0141 0.9951 18.500 1.1210 0.06283 0.05778 0.0873 0.0138 0.9957 18.750 1.1200 0.06622 0.06132 0.0863 0.0136 0.9963 19.000 1.1169 0.06996 0.06521 0.0850 0.0134 0.9969 19.250 1.1120 0.07406 0.06945 0.0835 0.0132 0.9975