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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2050 0.07124 0.06729 -0.0784 0.9993 0.0132 -19.500 -1.2069 0.06749 0.06343 -0.0798 0.9988 0.0134 -19.250 -1.2068 0.06414 0.05998 -0.0810 0.9983 0.0136 -19.000 -1.2049 0.06110 0.05684 -0.0820 0.9978 0.0139 -18.750 -1.2017 0.05827 0.05392 -0.0828 0.9973 0.0141 -18.500 -1.1964 0.05575 0.05130 -0.0835 0.9967 0.0144 -18.250 -1.1902 0.05339 0.04883 -0.0841 0.9962 0.0146 -18.000 -1.1821 0.05126 0.04660 -0.0847 0.9957 0.0148 -17.750 -1.1874 0.04792 0.04316 -0.0845 0.9952 0.0152 -17.500 -1.1820 0.04563 0.04079 -0.0847 0.9947 0.0155 -17.250 -1.1720 0.04380 0.03890 -0.0850 0.9943 0.0159 -17.000 -1.1593 0.04225 0.03730 -0.0854 0.9940 0.0162 -16.750 -1.1487 0.04080 0.03579 -0.0851 0.9932 0.0166 -16.500 -1.1390 0.03942 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0.8864 2.500 0.2412 0.00652 0.00307 0.0069 0.8047 0.8881 2.750 0.2621 0.00657 0.00313 0.0083 0.7971 0.8902 3.000 0.2801 0.00660 0.00317 0.0104 0.7877 0.8927 3.250 0.2923 0.00662 0.00316 0.0139 0.7755 0.8962 3.500 0.2965 0.00660 0.00309 0.0192 0.7611 0.9003 3.750 0.3129 0.00672 0.00319 0.0216 0.7406 0.9027 4.000 0.3266 0.00694 0.00334 0.0247 0.7125 0.9052 4.250 0.3349 0.00721 0.00351 0.0289 0.6799 0.9085 4.500 0.3345 0.00750 0.00365 0.0350 0.6400 0.9130 4.750 0.3311 0.00796 0.00391 0.0416 0.5862 0.9171 5.000 0.3317 0.00866 0.00436 0.0471 0.5200 0.9204 5.250 0.3335 0.00933 0.00476 0.0522 0.4534 0.9241 5.500 0.3350 0.00992 0.00508 0.0573 0.3870 0.9284 6.000 0.3552 0.01117 0.00582 0.0634 0.2592 0.9338 6.250 0.3696 0.01174 0.00619 0.0655 0.2100 0.9362 6.500 0.3846 0.01223 0.00651 0.0675 0.1732 0.9389 6.750 0.3997 0.01260 0.00678 0.0696 0.1461 0.9421 7.000 0.4161 0.01294 0.00702 0.0714 0.1235 0.9448 7.250 0.4364 0.01335 0.00734 0.0722 0.1026 0.9465 7.500 0.4566 0.01380 0.00771 0.0731 0.0840 0.9481 7.750 0.4768 0.01424 0.00808 0.0740 0.0690 0.9500 8.000 0.4959 0.01467 0.00845 0.0751 0.0576 0.9522 8.250 0.5134 0.01504 0.00879 0.0766 0.0509 0.9551 8.500 0.5286 0.01534 0.00906 0.0786 0.0470 0.9581 8.750 0.5507 0.01575 0.00948 0.0790 0.0437 0.9595 9.000 0.5745 0.01614 0.00990 0.0791 0.0417 0.9607 9.250 0.5974 0.01660 0.01036 0.0792 0.0398 0.9619 9.500 0.6172 0.01720 0.01096 0.0799 0.0374 0.9634 9.750 0.6403 0.01756 0.01135 0.0801 0.0366 0.9649 10.000 0.6610 0.01796 0.01178 0.0807 0.0355 0.9669 10.250 0.6710 0.01828 0.01213 0.0837 0.0346 0.9711 10.500 0.6950 0.01879 0.01264 0.0834 0.0334 0.9719 10.750 0.7165 0.01950 0.01337 0.0835 0.0319 0.9727 11.000 0.7393 0.02011 0.01402 0.0833 0.0311 0.9733 11.250 0.7642 0.02060 0.01455 0.0828 0.0303 0.9739 11.500 0.7886 0.02114 0.01513 0.0822 0.0294 0.9745 11.750 0.8135 0.02170 0.01570 0.0816 0.0284 0.9750 12.000 0.8367 0.02236 0.01638 0.0811 0.0276 0.9755 12.250 0.8531 0.02343 0.01749 0.0816 0.0264 0.9763 12.500 0.8749 0.02407 0.01818 0.0814 0.0259 0.9772 12.750 0.8966 0.02463 0.01879 0.0813 0.0253 0.9783 13.000 0.9164 0.02519 0.01939 0.0816 0.0246 0.9798 13.250 0.9252 0.02575 0.01997 0.0843 0.0240 0.9834 13.500 0.9480 0.02644 0.02069 0.0837 0.0233 0.9837 13.750 0.9676 0.02734 0.02161 0.0834 0.0225 0.9841 14.000 0.9804 0.02869 0.02302 0.0840 0.0218 0.9845 14.250 1.0024 0.02938 0.02378 0.0835 0.0214 0.9849 14.500 1.0228 0.03017 0.02462 0.0831 0.0208 0.9854 14.750 1.0419 0.03103 0.02555 0.0829 0.0202 0.9859 15.000 1.0611 0.03188 0.02643 0.0826 0.0197 0.9865 15.250 1.0791 0.03280 0.02739 0.0824 0.0191 0.9872 15.500 1.0932 0.03403 0.02864 0.0826 0.0186 0.9880 15.750 1.0999 0.03581 0.03050 0.0835 0.0180 0.9889 16.000 1.1159 0.03687 0.03164 0.0834 0.0177 0.9898 16.250 1.1296 0.03806 0.03291 0.0836 0.0173 0.9909 16.500 1.1417 0.03933 0.03425 0.0840 0.0169 0.9921 16.750 1.1508 0.04071 0.03570 0.0849 0.0166 0.9935 17.000 1.1632 0.04213 0.03717 0.0848 0.0162 0.9941 17.250 1.1756 0.04370 0.03881 0.0844 0.0158 0.9944 17.500 1.1856 0.04554 0.04070 0.0841 0.0155 0.9948 17.750 1.1908 0.04786 0.04309 0.0839 0.0151 0.9953 18.000 1.1849 0.05125 0.04659 0.0841 0.0147 0.9958 18.250 1.1943 0.05325 0.04869 0.0835 0.0146 0.9963 18.500 1.2016 0.05550 0.05104 0.0829 0.0143 0.9969 18.750 1.2067 0.05805 0.05369 0.0822 0.0141 0.9974 19.000 1.2092 0.06094 0.05668 0.0814 0.0139 0.9980 19.250 1.2117 0.06392 0.05976 0.0804 0.0136 0.9985