XFOIL Version 6.96 Calculated polar for: NACA 66(4)-221 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 -0.9605 0.06708 0.06205 -0.1052 0.8285 0.0139 -19.500 -0.9612 0.06417 0.05903 -0.1059 0.8241 0.0138 -19.250 -0.9577 0.06172 0.05650 -0.1066 0.8206 0.0140 -19.000 -0.9548 0.05929 0.05398 -0.1071 0.8168 0.0140 -18.750 -0.9506 0.05706 0.05166 -0.1075 0.8127 0.0142 -18.500 -0.9471 0.05483 0.04933 -0.1078 0.8087 0.0142 -18.250 -0.9454 0.05249 0.04690 -0.1078 0.8049 0.0142 -18.000 -0.9384 0.05065 0.04498 -0.1080 0.8019 0.0143 -17.750 -0.9330 0.04874 0.04300 -0.1080 0.7986 0.0143 -17.500 -0.9250 0.04711 0.04130 -0.1079 0.7951 0.0144 -17.250 -0.9189 0.04538 0.03948 -0.1077 0.7916 0.0145 -17.000 -0.9127 0.04370 0.03773 -0.1073 0.7882 0.0145 -16.750 -0.9069 0.04201 0.03598 -0.1069 0.7854 0.0148 -16.500 -0.8992 0.04051 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0.6779 0.6997 2.750 0.4833 0.00723 0.00270 -0.0441 0.6749 0.7003 3.000 0.5112 0.00722 0.00271 -0.0444 0.6720 0.7009 3.250 0.5391 0.00722 0.00273 -0.0447 0.6692 0.7014 3.500 0.5666 0.00722 0.00271 -0.0449 0.6649 0.7019 3.750 0.5929 0.00722 0.00274 -0.0449 0.6597 0.7024 4.000 0.6187 0.00722 0.00276 -0.0448 0.6524 0.7028 4.250 0.6434 0.00723 0.00277 -0.0445 0.6446 0.7033 4.500 0.6651 0.00725 0.00278 -0.0435 0.6290 0.7043 4.750 0.6694 0.00745 0.00284 -0.0390 0.5827 0.7054 5.000 0.6409 0.00808 0.00324 -0.0280 0.5354 0.7069 5.250 0.6236 0.00896 0.00395 -0.0199 0.4940 0.7082 5.500 0.6062 0.01005 0.00485 -0.0124 0.4501 0.7094 5.750 0.5956 0.01113 0.00577 -0.0064 0.4104 0.7107 6.000 0.5851 0.01234 0.00678 -0.0007 0.3645 0.7119 6.250 0.5782 0.01353 0.00776 0.0042 0.3216 0.7131 6.500 0.5802 0.01447 0.00855 0.0076 0.2877 0.7142 6.750 0.5814 0.01547 0.00938 0.0110 0.2505 0.7153 7.000 0.5841 0.01645 0.01017 0.0142 0.2107 0.7164 7.250 0.5877 0.01745 0.01098 0.0170 0.1731 0.7174 7.500 0.5972 0.01823 0.01164 0.0190 0.1456 0.7183 7.750 0.6016 0.01927 0.01246 0.0217 0.1060 0.7193 8.000 0.6132 0.02003 0.01311 0.0233 0.0859 0.7201 8.250 0.6259 0.02076 0.01375 0.0247 0.0678 0.7210 8.500 0.6406 0.02139 0.01432 0.0259 0.0549 0.7223 8.750 0.6547 0.02207 0.01495 0.0271 0.0437 0.7238 9.000 0.6703 0.02269 0.01556 0.0281 0.0371 0.7253 9.250 0.6867 0.02328 0.01613 0.0290 0.0327 0.7265 9.500 0.7036 0.02385 0.01670 0.0297 0.0297 0.7278 9.750 0.7208 0.02443 0.01728 0.0305 0.0275 0.7291 10.000 0.7375 0.02504 0.01791 0.0312 0.0257 0.7305 10.250 0.7544 0.02566 0.01854 0.0319 0.0244 0.7319 10.500 0.7708 0.02631 0.01918 0.0326 0.0228 0.7332 10.750 0.7883 0.02691 0.01980 0.0332 0.0219 0.7346 11.000 0.8052 0.02755 0.02044 0.0338 0.0203 0.7360 11.250 0.8210 0.02827 0.02117 0.0345 0.0195 0.7373 11.500 0.8371 0.02898 0.02190 0.0351 0.0184 0.7385 11.750 0.8536 0.02968 0.02261 0.0357 0.0174 0.7395 12.000 0.8693 0.03042 0.02337 0.0364 0.0166 0.7414 12.250 0.8849 0.03116 0.02413 0.0370 0.0162 0.7433 12.500 0.9002 0.03195 0.02496 0.0376 0.0156 0.7452 12.750 0.9152 0.03277 0.02581 0.0382 0.0153 0.7472 13.000 0.9299 0.03362 0.02669 0.0388 0.0145 0.7490 13.250 0.9445 0.03449 0.02759 0.0394 0.0140 0.7510 13.500 0.9592 0.03537 0.02850 0.0400 0.0139 0.7530 13.750 0.9723 0.03639 0.02954 0.0406 0.0136 0.7548 14.000 0.9855 0.03740 0.03059 0.0412 0.0131 0.7566 14.250 0.9996 0.03838 0.03160 0.0416 0.0127 0.7581 14.500 1.0127 0.03941 0.03269 0.0422 0.0127 0.7605 14.750 1.0246 0.04056 0.03388 0.0427 0.0125 0.7630 15.000 1.0366 0.04172 0.03510 0.0432 0.0123 0.7655 15.250 1.0494 0.04284 0.03626 0.0437 0.0120 0.7681 15.500 1.0602 0.04414 0.03762 0.0442 0.0119 0.7706 15.750 1.0708 0.04548 0.03900 0.0446 0.0117 0.7731 16.000 1.0815 0.04684 0.04040 0.0450 0.0116 0.7754 16.250 1.0905 0.04838 0.04198 0.0454 0.0114 0.7775 16.500 1.0984 0.05001 0.04367 0.0458 0.0111 0.7805 16.750 1.1067 0.05165 0.04538 0.0461 0.0110 0.7835 17.000 1.1142 0.05340 0.04720 0.0464 0.0111 0.7868 17.250 1.1201 0.05534 0.04920 0.0467 0.0109 0.7901 17.500 1.1285 0.05709 0.05103 0.0467 0.0109 0.7932 17.750 1.1369 0.05887 0.05286 0.0467 0.0108 0.7961 18.000 1.1411 0.06110 0.05519 0.0467 0.0107 0.7996 18.250 1.1464 0.06326 0.05743 0.0467 0.0107 0.8031 18.500 1.1524 0.06540 0.05965 0.0465 0.0106 0.8071 18.750 1.1573 0.06770 0.06202 0.0462 0.0105 0.8108 19.000 1.1612 0.07016 0.06457 0.0459 0.0104 0.8140 19.250 1.1621 0.07301 0.06751 0.0454 0.0104 0.8172