XFOIL Version 6.96 Calculated polar for: NACA 63-215 AIRFOIL 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 -1.0256 0.12210 0.11948 -0.0120 1.0000 0.0124 -19.500 -1.0434 0.11429 0.11155 -0.0167 1.0000 0.0124 -19.250 -1.0621 0.10660 0.10373 -0.0212 1.0000 0.0125 -19.000 -1.0750 0.10015 0.09718 -0.0249 1.0000 0.0126 -18.750 -1.0873 0.09395 0.09088 -0.0285 1.0000 0.0126 -18.500 -1.0987 0.08810 0.08492 -0.0317 1.0000 0.0127 -18.250 -1.1104 0.08239 0.07911 -0.0348 1.0000 0.0128 -18.000 -1.1174 0.07754 0.07417 -0.0374 1.0000 0.0129 -17.750 -1.1238 0.07295 0.06949 -0.0397 1.0000 0.0130 -17.500 -1.1319 0.06828 0.06471 -0.0419 1.0000 0.0130 -17.250 -1.1346 0.06444 0.06079 -0.0438 1.0000 0.0132 -17.000 -1.1398 0.06048 0.05673 -0.0455 1.0000 0.0132 -16.750 -1.1417 0.05700 0.05316 -0.0469 1.0000 0.0134 -16.500 -1.1425 0.05378 0.04985 -0.0482 1.0000 0.0135 -16.250 -1.1420 0.05082 0.04680 -0.0492 1.0000 0.0137 -16.000 -1.1409 0.04802 0.04391 -0.0501 1.0000 0.0139 -15.750 -1.1419 0.04513 0.04093 -0.0507 1.0000 0.0140 -15.500 -1.1375 0.04290 0.03861 -0.0512 1.0000 0.0142 -15.250 -1.1341 0.04063 0.03626 -0.0516 1.0000 0.0143 -15.000 -1.1265 0.03882 0.03437 -0.0519 1.0000 0.0145 -14.750 -1.1221 0.03675 0.03222 -0.0520 1.0000 0.0147 -14.500 -1.1261 0.03401 0.02938 -0.0518 1.0000 0.0150 -14.250 -1.1229 0.03198 0.02729 -0.0515 1.0000 0.0152 -14.000 -1.1174 0.03020 0.02547 -0.0513 1.0000 0.0155 -13.750 -1.1098 0.02866 0.02387 -0.0509 1.0000 0.0157 -13.500 -1.0993 0.02739 0.02256 -0.0505 1.0000 0.0160 -13.250 -1.0891 0.02615 0.02128 -0.0500 1.0000 0.0163 -13.000 -1.0785 0.02497 0.02005 -0.0493 1.0000 0.0166 -12.750 -1.0680 0.02383 0.01886 -0.0486 1.0000 0.0170 -12.500 -1.0571 0.02277 0.01774 -0.0477 1.0000 0.0172 -12.250 -1.0441 0.02190 0.01682 -0.0469 1.0000 0.0175 -12.000 -1.0309 0.02109 0.01595 -0.0459 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0.5285 0.6797 3.250 0.5530 0.00669 0.00186 -0.0427 0.5183 0.6859 3.500 0.5814 0.00674 0.00193 -0.0429 0.5050 0.6925 3.750 0.6098 0.00684 0.00201 -0.0430 0.4904 0.6994 4.000 0.6380 0.00695 0.00210 -0.0431 0.4748 0.7059 4.250 0.6661 0.00706 0.00220 -0.0432 0.4601 0.7126 4.500 0.6942 0.00720 0.00232 -0.0433 0.4435 0.7193 4.750 0.7217 0.00735 0.00245 -0.0433 0.4244 0.7261 5.000 0.7488 0.00757 0.00261 -0.0433 0.4006 0.7332 5.250 0.7749 0.00788 0.00281 -0.0432 0.3661 0.7398 5.500 0.7988 0.00839 0.00312 -0.0428 0.3142 0.7469 5.750 0.8215 0.00903 0.00350 -0.0422 0.2567 0.7540 6.000 0.8434 0.00969 0.00393 -0.0416 0.2039 0.7612 6.250 0.8654 0.01035 0.00436 -0.0409 0.1569 0.7686 6.500 0.8870 0.01097 0.00479 -0.0402 0.1172 0.7758 6.750 0.9091 0.01154 0.00522 -0.0395 0.0877 0.7838 7.000 0.9314 0.01205 0.00564 -0.0389 0.0668 0.7913 7.250 0.9541 0.01250 0.00604 -0.0382 0.0533 0.7996 7.500 0.9769 0.01291 0.00644 -0.0376 0.0455 0.8076 7.750 0.9997 0.01331 0.00683 -0.0370 0.0409 0.8164 8.000 1.0224 0.01366 0.00722 -0.0363 0.0377 0.8249 8.250 1.0449 0.01402 0.00761 -0.0356 0.0354 0.8345 8.500 1.0646 0.01451 0.00813 -0.0345 0.0326 0.8446 8.750 1.0867 0.01481 0.00850 -0.0337 0.0314 0.8550 9.000 1.1073 0.01517 0.00891 -0.0327 0.0298 0.8670 9.250 1.1245 0.01564 0.00943 -0.0312 0.0281 0.8810 9.500 1.1402 0.01611 0.00998 -0.0293 0.0267 0.8979 9.750 1.1542 0.01639 0.01037 -0.0271 0.0256 0.9211 10.000 1.1689 0.01670 0.01079 -0.0251 0.0244 1.0000 10.250 1.1806 0.01739 0.01148 -0.0231 0.0230 1.0000 10.500 1.1933 0.01808 0.01220 -0.0214 0.0221 1.0000 10.750 1.2084 0.01867 0.01283 -0.0200 0.0212 1.0000 11.000 1.2225 0.01934 0.01353 -0.0187 0.0204 1.0000 11.250 1.2352 0.02013 0.01433 -0.0173 0.0197 1.0000 11.500 1.2411 0.02138 0.01562 -0.0154 0.0186 1.0000 11.750 1.2520 0.02239 0.01668 -0.0141 0.0183 1.0000 12.000 1.2646 0.02332 0.01767 -0.0131 0.0179 1.0000 12.250 1.2767 0.02433 0.01872 -0.0121 0.0174 1.0000 12.500 1.2874 0.02547 0.01990 -0.0111 0.0170 1.0000 12.750 1.2981 0.02665 0.02112 -0.0102 0.0165 1.0000 13.000 1.3071 0.02800 0.02251 -0.0093 0.0160 1.0000 13.250 1.3142 0.02954 0.02409 -0.0084 0.0157 1.0000 13.500 1.3152 0.03166 0.02628 -0.0073 0.0153 1.0000 13.750 1.3197 0.03354 0.02823 -0.0066 0.0150 1.0000 14.000 1.3265 0.03528 0.03004 -0.0061 0.0149 1.0000 14.250 1.3357 0.03685 0.03167 -0.0057 0.0146 1.0000 14.500 1.3421 0.03870 0.03360 -0.0054 0.0144 1.0000 14.750 1.3481 0.04066 0.03561 -0.0051 0.0141 1.0000 15.000 1.3519 0.04288 0.03792 -0.0050 0.0139 1.0000 15.250 1.3572 0.04503 0.04012 -0.0050 0.0136 1.0000 15.500 1.3605 0.04746 0.04263 -0.0051 0.0135 1.0000 15.750 1.3641 0.04995 0.04518 -0.0053 0.0133 1.0000 16.000 1.3676 0.05251 0.04781 -0.0057 0.0132 1.0000 16.250 1.3684 0.05545 0.05083 -0.0062 0.0130 1.0000 16.500 1.3687 0.05856 0.05400 -0.0068 0.0128 1.0000 16.750 1.3668 0.06204 0.05757 -0.0077 0.0127 1.0000 17.000 1.3611 0.06609 0.06170 -0.0088 0.0125 1.0000 17.250 1.3550 0.07033 0.06603 -0.0101 0.0123 1.0000 17.500 1.3454 0.07516 0.07099 -0.0117 0.0121 1.0000 17.750 1.3444 0.07898 0.07490 -0.0132 0.0121 1.0000 18.000 1.3420 0.08306 0.07908 -0.0148 0.0120 1.0000 18.250 1.3397 0.08728 0.08340 -0.0167 0.0120 1.0000 18.500 1.3356 0.09183 0.08806 -0.0187 0.0119 1.0000 18.750 1.3320 0.09642 0.09275 -0.0209 0.0118 1.0000 19.000 1.3257 0.10153 0.09797 -0.0234 0.0118 1.0000 19.250 1.3204 0.10660 0.10314 -0.0260 0.0117 1.0000