XFOIL Version 6.96 Calculated polar for: NACA 65(4)-421 a=0.5 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -0.8571 0.08708 0.08264 -0.0781 0.8349 0.0213 -19.250 -0.8619 0.08282 0.07825 -0.0805 0.8294 0.0214 -19.000 -0.8652 0.07883 0.07414 -0.0827 0.8240 0.0216 -18.750 -0.8687 0.07500 0.07019 -0.0846 0.8183 0.0217 -18.500 -0.8711 0.07146 0.06650 -0.0862 0.8126 0.0219 -18.250 -0.8721 0.06813 0.06306 -0.0877 0.8073 0.0221 -18.000 -0.8720 0.06507 0.05987 -0.0891 0.8016 0.0224 -17.750 -0.8719 0.06213 0.05680 -0.0901 0.7960 0.0225 -17.500 -0.8706 0.05940 0.05393 -0.0911 0.7909 0.0228 -17.250 -0.8685 0.05681 0.05120 -0.0919 0.7859 0.0230 -17.000 -0.8654 0.05442 0.04869 -0.0925 0.7807 0.0232 -16.750 -0.8618 0.05216 0.04628 -0.0930 0.7759 0.0235 -16.500 -0.8566 0.05011 0.04410 -0.0933 0.7715 0.0236 -16.250 -0.8512 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0.00953 0.00326 -0.0533 0.6107 0.6001 -1.500 0.1313 0.00956 0.00324 -0.0537 0.6092 0.6031 -1.250 0.1604 0.00957 0.00323 -0.0542 0.6077 0.6056 -1.000 0.1893 0.00956 0.00324 -0.0546 0.6062 0.6082 -0.750 0.2181 0.00956 0.00325 -0.0550 0.6047 0.6112 -0.500 0.2469 0.00957 0.00327 -0.0554 0.6032 0.6143 -0.250 0.2757 0.00959 0.00329 -0.0558 0.6017 0.6173 0.000 0.3046 0.00962 0.00330 -0.0563 0.6002 0.6203 0.250 0.3335 0.00965 0.00331 -0.0567 0.5985 0.6233 0.500 0.3623 0.00968 0.00332 -0.0571 0.5969 0.6261 0.750 0.3910 0.00970 0.00335 -0.0575 0.5954 0.6292 1.000 0.4197 0.00974 0.00339 -0.0579 0.5940 0.6327 1.250 0.4486 0.00980 0.00344 -0.0584 0.5926 0.6362 1.500 0.4770 0.00984 0.00351 -0.0588 0.5913 0.6396 1.750 0.5054 0.00989 0.00358 -0.0592 0.5898 0.6429 2.000 0.5336 0.00993 0.00366 -0.0595 0.5881 0.6460 2.250 0.5616 0.00996 0.00374 -0.0598 0.5864 0.6494 2.500 0.5897 0.01001 0.00382 -0.0602 0.5848 0.6531 2.750 0.6178 0.01007 0.00391 -0.0605 0.5832 0.6572 3.000 0.6460 0.01013 0.00399 -0.0608 0.5816 0.6614 3.250 0.6741 0.01018 0.00406 -0.0612 0.5800 0.6654 3.500 0.7021 0.01023 0.00414 -0.0615 0.5783 0.6695 3.750 0.7304 0.01031 0.00424 -0.0619 0.5769 0.6738 4.000 0.7585 0.01040 0.00436 -0.0622 0.5753 0.6782 4.250 0.7853 0.01048 0.00450 -0.0624 0.5736 0.6825 4.500 0.8118 0.01054 0.00465 -0.0625 0.5716 0.6868 4.750 0.8383 0.01061 0.00479 -0.0625 0.5695 0.6915 5.000 0.8648 0.01069 0.00492 -0.0626 0.5672 0.6966 5.250 0.8913 0.01076 0.00503 -0.0627 0.5647 0.7019 5.500 0.9177 0.01080 0.00513 -0.0627 0.5620 0.7071 5.750 0.9442 0.01087 0.00522 -0.0628 0.5587 0.7128 6.000 0.9664 0.01095 0.00540 -0.0621 0.5542 0.7187 6.250 0.9890 0.01101 0.00552 -0.0614 0.5492 0.7240 6.500 1.0118 0.01105 0.00557 -0.0607 0.5434 0.7298 6.750 1.0292 0.01114 0.00577 -0.0592 0.5352 0.7363 7.250 1.0539 0.01139 0.00610 -0.0541 0.5168 0.7495 7.500 1.0613 0.01169 0.00642 -0.0508 0.5057 0.7576 7.750 1.0649 0.01215 0.00689 -0.0471 0.4898 0.7658 8.000 1.0659 0.01279 0.00751 -0.0432 0.4706 0.7749 8.250 1.0598 0.01379 0.00844 -0.0386 0.4469 0.7844 8.500 1.0507 0.01506 0.00965 -0.0338 0.4198 0.7949 8.750 1.0307 0.01697 0.01143 -0.0281 0.3862 0.8063 9.000 1.0125 0.01903 0.01338 -0.0230 0.3553 0.8193 9.250 0.9959 0.02116 0.01544 -0.0185 0.3261 0.8331 9.500 0.9857 0.02311 0.01733 -0.0149 0.3020 0.8480 9.750 0.9688 0.02555 0.01968 -0.0108 0.2696 0.8662 10.000 0.9597 0.02768 0.02175 -0.0078 0.2418 0.8889 10.250 0.9590 0.02969 0.02373 -0.0062 0.2170 0.9202 10.500 0.9742 0.03243 0.02636 -0.0092 0.1812 0.9542 11.000 0.9831 0.03636 0.03008 -0.0080 0.1383 1.0000 11.250 0.9850 0.03831 0.03192 -0.0068 0.1180 1.0000 11.500 0.9882 0.04018 0.03368 -0.0057 0.0990 1.0000 11.750 0.9898 0.04224 0.03562 -0.0046 0.0790 1.0000 12.000 0.9936 0.04416 0.03744 -0.0037 0.0631 1.0000 12.250 0.9983 0.04603 0.03922 -0.0029 0.0487 1.0000 12.500 1.0033 0.04794 0.04107 -0.0022 0.0381 1.0000 13.000 1.0210 0.05118 0.04429 -0.0013 0.0296 1.0000 13.250 1.0301 0.05283 0.04596 -0.0010 0.0274 1.0000 13.500 1.0401 0.05441 0.04755 -0.0007 0.0257 1.0000 13.750 1.0491 0.05609 0.04924 -0.0004 0.0239 1.0000 14.000 1.0589 0.05774 0.05093 -0.0002 0.0230 1.0000 14.250 1.0679 0.05949 0.05271 0.0000 0.0220 1.0000 14.500 1.0761 0.06132 0.05456 0.0002 0.0211 1.0000 14.750 1.0851 0.06310 0.05638 0.0003 0.0205 1.0000 15.000 1.0938 0.06494 0.05827 0.0004 0.0196 1.0000 15.250 1.1023 0.06681 0.06018 0.0004 0.0189 1.0000 15.500 1.1101 0.06878 0.06220 0.0004 0.0187 1.0000 15.750 1.1162 0.07098 0.06442 0.0004 0.0180 1.0000 16.000 1.1225 0.07316 0.06664 0.0003 0.0177 1.0000 16.250 1.1294 0.07532 0.06886 0.0002 0.0174 1.0000 16.500 1.1361 0.07752 0.07112 0.0000 0.0169 1.0000 16.750 1.1422 0.07981 0.07347 -0.0002 0.0168 1.0000 17.000 1.1479 0.08219 0.07591 -0.0005 0.0165 1.0000 17.250 1.1535 0.08461 0.07839 -0.0009 0.0161 1.0000 17.500 1.1578 0.08720 0.08103 -0.0013 0.0158 1.0000 17.750 1.1621 0.08982 0.08372 -0.0018 0.0157 1.0000 18.000 1.1660 0.09251 0.08646 -0.0023 0.0154 1.0000 18.250 1.1678 0.09551 0.08951 -0.0030 0.0152 1.0000 18.500 1.1701 0.09849 0.09254 -0.0037 0.0149 1.0000