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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2109 0.05796 0.05341 -0.0964 0.9949 0.0092 -19.500 -1.2101 0.05504 0.05039 -0.0971 0.9946 0.0094 -19.250 -1.2072 0.05239 0.04766 -0.0976 0.9943 0.0096 -19.000 -1.2027 0.04996 0.04515 -0.0981 0.9940 0.0098 -18.750 -1.1987 0.04778 0.04288 -0.0980 0.9932 0.0101 -18.500 -1.1938 0.04578 0.04080 -0.0977 0.9922 0.0104 -18.250 -1.1872 0.04393 0.03887 -0.0974 0.9913 0.0106 -18.000 -1.1796 0.04217 0.03703 -0.0972 0.9905 0.0108 -17.750 -1.1719 0.04043 0.03522 -0.0969 0.9897 0.0112 -17.500 -1.1626 0.03883 0.03356 -0.0967 0.9889 0.0116 -17.250 -1.1518 0.03734 0.03202 -0.0965 0.9882 0.0121 -17.000 -1.1396 0.03595 0.03058 -0.0964 0.9876 0.0125 -16.750 -1.1266 0.03467 0.02924 -0.0963 0.9870 0.0129 -16.500 -1.1127 0.03346 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0.8619 2.500 0.1750 0.00611 0.00220 0.0220 0.7291 0.8651 2.750 0.1838 0.00627 0.00227 0.0262 0.7032 0.8689 3.000 0.1921 0.00644 0.00234 0.0304 0.6762 0.8727 3.250 0.1963 0.00681 0.00255 0.0355 0.6295 0.8760 3.500 0.1951 0.00733 0.00285 0.0416 0.5700 0.8801 3.750 0.1981 0.00783 0.00312 0.0466 0.5118 0.8843 4.000 0.2028 0.00833 0.00338 0.0511 0.4521 0.8880 4.250 0.2116 0.00893 0.00372 0.0546 0.3804 0.8910 4.500 0.2216 0.00951 0.00404 0.0578 0.3128 0.8943 4.750 0.2352 0.00997 0.00430 0.0602 0.2615 0.8975 5.000 0.2511 0.01036 0.00452 0.0622 0.2198 0.9004 5.250 0.2680 0.01072 0.00473 0.0639 0.1838 0.9031 5.500 0.2884 0.01105 0.00498 0.0649 0.1585 0.9055 5.750 0.3087 0.01137 0.00523 0.0659 0.1372 0.9079 6.250 0.3492 0.01196 0.00569 0.0679 0.1037 0.9129 6.500 0.3697 0.01223 0.00591 0.0689 0.0911 0.9156 6.750 0.3904 0.01249 0.00612 0.0698 0.0806 0.9180 7.000 0.4122 0.01279 0.00639 0.0704 0.0708 0.9200 7.250 0.4331 0.01311 0.00669 0.0712 0.0607 0.9221 7.500 0.4538 0.01344 0.00698 0.0720 0.0527 0.9244 7.750 0.4743 0.01375 0.00726 0.0729 0.0468 0.9270 8.000 0.4954 0.01402 0.00753 0.0737 0.0435 0.9295 8.250 0.5158 0.01431 0.00781 0.0745 0.0406 0.9319 8.500 0.5367 0.01463 0.00813 0.0752 0.0381 0.9338 8.750 0.5585 0.01494 0.00847 0.0758 0.0369 0.9358 9.000 0.5797 0.01527 0.00881 0.0765 0.0355 0.9379 9.250 0.6001 0.01561 0.00917 0.0772 0.0342 0.9402 9.500 0.6200 0.01596 0.00952 0.0781 0.0330 0.9425 9.750 0.6390 0.01634 0.00992 0.0791 0.0316 0.9449 10.000 0.6587 0.01667 0.01027 0.0800 0.0311 0.9472 10.250 0.6797 0.01704 0.01068 0.0805 0.0304 0.9489 10.500 0.7003 0.01743 0.01110 0.0812 0.0295 0.9507 10.750 0.7201 0.01783 0.01152 0.0819 0.0287 0.9526 11.000 0.7390 0.01826 0.01196 0.0828 0.0279 0.9547 11.250 0.7566 0.01872 0.01245 0.0839 0.0269 0.9572 11.500 0.7729 0.01922 0.01297 0.0852 0.0261 0.9597 11.750 0.7927 0.01964 0.01343 0.0858 0.0257 0.9614 12.000 0.8129 0.02010 0.01393 0.0863 0.0252 0.9628 12.250 0.8322 0.02059 0.01445 0.0869 0.0245 0.9644 12.500 0.8509 0.02109 0.01499 0.0876 0.0237 0.9661 12.750 0.8689 0.02161 0.01553 0.0884 0.0230 0.9682 13.000 0.8854 0.02216 0.01610 0.0894 0.0223 0.9704 13.250 0.8992 0.02277 0.01674 0.0909 0.0215 0.9728 13.500 0.9190 0.02336 0.01737 0.0912 0.0210 0.9738 13.750 0.9383 0.02396 0.01802 0.0915 0.0204 0.9748 14.000 0.9569 0.02462 0.01872 0.0918 0.0197 0.9759 14.250 0.9751 0.02531 0.01944 0.0921 0.0190 0.9772 14.500 0.9929 0.02601 0.02017 0.0925 0.0183 0.9785 14.750 1.0088 0.02680 0.02098 0.0931 0.0175 0.9799 15.000 1.0238 0.02757 0.02180 0.0939 0.0169 0.9815 15.250 1.0366 0.02833 0.02261 0.0952 0.0164 0.9836 15.500 1.0531 0.02922 0.02354 0.0954 0.0157 0.9844 15.750 1.0702 0.03016 0.02451 0.0954 0.0150 0.9850 16.000 1.0862 0.03118 0.02556 0.0955 0.0143 0.9855 16.250 1.1009 0.03229 0.02672 0.0956 0.0137 0.9861 16.500 1.1158 0.03341 0.02791 0.0957 0.0134 0.9866 16.750 1.1297 0.03462 0.02918 0.0958 0.0129 0.9871 17.000 1.1429 0.03590 0.03052 0.0959 0.0125 0.9877 17.250 1.1551 0.03728 0.03195 0.0960 0.0120 0.9884 17.500 1.1659 0.03876 0.03349 0.0961 0.0115 0.9891 17.750 1.1752 0.04037 0.03515 0.0964 0.0112 0.9899 18.000 1.1830 0.04209 0.03695 0.0967 0.0108 0.9907 18.250 1.1908 0.04383 0.03877 0.0969 0.0106 0.9916 18.500 1.1973 0.04567 0.04070 0.0972 0.0103 0.9925 18.750 1.2022 0.04766 0.04276 0.0975 0.0100 0.9935 19.000 1.2071 0.04986 0.04505 0.0974 0.0098 0.9941 19.250 1.2115 0.05229 0.04756 0.0969 0.0095 0.9944