XFOIL Version 6.96 Calculated polar for: NACA 66(2)-415 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3884 0.08377 0.07990 -0.0975 0.9556 0.0237 -12.000 -0.4388 0.06521 0.06110 -0.1130 0.9478 0.0229 -11.750 -0.4705 0.05732 0.05291 -0.1179 0.9372 0.0227 -11.500 -0.4878 0.05278 0.04813 -0.1192 0.9275 0.0229 -11.250 -0.5040 0.04886 0.04392 -0.1190 0.9185 0.0230 -11.000 -0.5196 0.04578 0.04059 -0.1168 0.9090 0.0231 -10.500 -0.5438 0.04075 0.03500 -0.1101 0.8933 0.0234 -10.250 -0.5500 0.03850 0.03243 -0.1066 0.8875 0.0238 -10.000 -0.5501 0.03628 0.02988 -0.1037 0.8820 0.0241 -9.750 -0.5467 0.03421 0.02744 -0.1010 0.8765 0.0245 -9.500 -0.5400 0.03233 0.02510 -0.0985 0.8722 0.0253 -9.250 -0.5268 0.03065 0.02314 -0.0970 0.8689 0.0259 -9.000 -0.5103 0.02934 0.02172 -0.0960 0.8650 0.0264 -8.750 -0.4920 0.02816 0.02039 -0.0951 0.8614 0.0269 -8.500 -0.4718 0.02703 0.01909 -0.0944 0.8584 0.0275 -8.250 -0.4498 0.02591 0.01781 -0.0939 0.8560 0.0281 -8.000 -0.4263 0.02483 0.01655 -0.0935 0.8539 0.0288 -7.750 -0.4039 0.02396 0.01554 -0.0930 0.8510 0.0297 -7.500 -0.3814 0.02324 0.01464 -0.0924 0.8480 0.0308 -7.250 -0.3577 0.02253 0.01380 -0.0920 0.8452 0.0315 -7.000 -0.3315 0.02138 0.01266 -0.0921 0.8429 0.0324 -6.750 -0.3076 0.02065 0.01190 -0.0918 0.8407 0.0334 -6.500 -0.2841 0.01999 0.01121 -0.0914 0.8386 0.0343 -6.250 -0.2622 0.01947 0.01065 -0.0907 0.8363 0.0356 -6.000 -0.2423 0.01906 0.01021 -0.0896 0.8333 0.0371 -5.750 -0.2219 0.01866 0.00975 -0.0886 0.8306 0.0384 -5.500 -0.2034 0.01811 0.00919 -0.0874 0.8281 0.0396 -5.250 -0.1845 0.01761 0.00869 -0.0862 0.8258 0.0410 -5.000 -0.1639 0.01722 0.00825 -0.0853 0.8239 0.0429 -4.750 -0.1419 0.01689 0.00787 -0.0845 0.8223 0.0455 -4.500 -0.1212 0.01662 0.00756 -0.0836 0.8202 0.0480 -4.250 -0.1030 0.01636 0.00731 -0.0822 0.8173 0.0513 -4.000 -0.0824 0.01614 0.00707 -0.0812 0.8147 0.0556 -3.750 -0.0615 0.01586 0.00683 -0.0803 0.8122 0.0651 -3.500 -0.0419 0.01540 0.00655 -0.0792 0.8102 0.1016 -3.250 -0.0292 0.01437 0.00618 -0.0774 0.8083 0.2591 -3.000 -0.0211 0.01299 0.00581 -0.0749 0.8065 0.4932 -2.750 -0.0054 0.01298 0.00655 -0.0718 0.8047 0.6828 -2.500 0.0143 0.01350 0.00715 -0.0698 0.8021 0.7252 -2.250 0.0358 0.01396 0.00759 -0.0683 0.7997 0.7486 -2.000 0.0591 0.01437 0.00800 -0.0669 0.7976 0.7612 -1.750 0.0830 0.01472 0.00833 -0.0657 0.7956 0.7728 -1.500 0.1080 0.01493 0.00847 -0.0650 0.7940 0.7840 -1.250 0.1340 0.01512 0.00865 -0.0644 0.7927 0.7879 -1.000 0.1614 0.01517 0.00865 -0.0645 0.7915 0.7909 -0.750 0.1895 0.01518 0.00861 -0.0648 0.7904 0.7939 -0.500 0.2141 0.01524 0.00863 -0.0647 0.7886 0.7974 -0.250 0.2325 0.01540 0.00878 -0.0636 0.7849 0.8006 0.000 0.2551 0.01553 0.00892 -0.0629 0.7825 0.8020 0.250 0.2800 0.01561 0.00898 -0.0626 0.7803 0.8036 0.500 0.3071 0.01563 0.00900 -0.0627 0.7785 0.8054 0.750 0.3360 0.01560 0.00896 -0.0632 0.7768 0.8070 1.000 0.3664 0.01554 0.00889 -0.0640 0.7754 0.8086 1.250 0.3975 0.01548 0.00882 -0.0649 0.7742 0.8103 1.500 0.4084 0.01586 0.00925 -0.0623 0.7684 0.8132 1.750 0.4332 0.01592 0.00933 -0.0622 0.7652 0.8158 2.000 0.4617 0.01588 0.00931 -0.0626 0.7628 0.8175 2.250 0.4923 0.01579 0.00927 -0.0632 0.7609 0.8188 2.500 0.5244 0.01569 0.00919 -0.0641 0.7592 0.8201 2.750 0.5384 0.01600 0.00958 -0.0619 0.7540 0.8222 3.000 0.5594 0.01613 0.00977 -0.0610 0.7496 0.8244 3.250 0.5895 0.01603 0.00973 -0.0615 0.7468 0.8262 3.500 0.6250 0.01576 0.00951 -0.0630 0.7443 0.8278 3.750 0.6429 0.01578 0.00960 -0.0614 0.7366 0.8306 4.000 0.6837 0.01502 0.00886 -0.0633 0.7287 0.8324 4.250 0.7006 0.01481 0.00873 -0.0610 0.7167 0.8347 4.500 0.7217 0.01451 0.00850 -0.0594 0.7040 0.8368 4.750 0.7412 0.01428 0.00834 -0.0576 0.6893 0.8392 5.000 0.7597 0.01393 0.00800 -0.0554 0.6653 0.8420 5.250 0.7649 0.01383 0.00788 -0.0509 0.6234 0.8458 5.750 0.7710 0.01484 0.00771 -0.0414 0.4287 0.8524 6.000 0.7633 0.01597 0.00851 -0.0357 0.3600 0.8568 6.250 0.7577 0.01725 0.00942 -0.0309 0.2895 0.8618 6.500 0.7544 0.01860 0.01039 -0.0267 0.2161 0.8665 6.750 0.7531 0.01992 0.01135 -0.0229 0.1439 0.8709 7.000 0.7561 0.02121 0.01230 -0.0199 0.0847 0.8756 7.250 0.7668 0.02219 0.01314 -0.0180 0.0593 0.8802 7.500 0.7788 0.02297 0.01389 -0.0161 0.0496 0.8840 7.750 0.7927 0.02367 0.01463 -0.0145 0.0445 0.8885 8.000 0.8063 0.02449 0.01546 -0.0131 0.0412 0.8936 8.250 0.8213 0.02520 0.01626 -0.0118 0.0385 0.8984 8.500 0.8344 0.02598 0.01711 -0.0102 0.0361 0.9038 8.750 0.8453 0.02701 0.01818 -0.0086 0.0341 0.9103 9.000 0.8581 0.02783 0.01909 -0.0070 0.0327 0.9170 9.250 0.8713 0.02869 0.02003 -0.0056 0.0311 0.9250 9.500 0.8839 0.02959 0.02100 -0.0042 0.0295 0.9338 9.750 0.8967 0.03059 0.02206 -0.0031 0.0283 0.9441 10.000 0.9093 0.03190 0.02338 -0.0022 0.0273 0.9565 10.250 0.9279 0.03283 0.02445 -0.0022 0.0264 0.9801 10.750 0.9617 0.03502 0.02678 -0.0012 0.0247 1.0000 11.000 0.9790 0.03615 0.02797 -0.0008 0.0238 1.0000 11.250 0.9959 0.03732 0.02916 -0.0005 0.0230 1.0000 11.500 1.0133 0.03859 0.03041 -0.0002 0.0222 1.0000 11.750 1.0316 0.03984 0.03177 0.0002 0.0216 1.0000 12.000 1.0499 0.04115 0.03322 0.0005 0.0209 1.0000 12.250 1.0679 0.04256 0.03478 0.0009 0.0204 1.0000 12.500 1.0851 0.04411 0.03647 0.0013 0.0200 1.0000 12.750 1.0999 0.04573 0.03826 0.0018 0.0195 1.0000 13.000 1.1129 0.04751 0.04019 0.0024 0.0191 1.0000 13.250 1.1243 0.04942 0.04226 0.0030 0.0188 1.0000 13.500 1.1333 0.05145 0.04444 0.0037 0.0186 1.0000 13.750 1.1404 0.05358 0.04673 0.0044 0.0183 1.0000 14.000 1.1457 0.05597 0.04928 0.0052 0.0182 1.0000 14.250 1.1490 0.05849 0.05196 0.0058 0.0180 1.0000 14.500 1.1502 0.06128 0.05492 0.0065 0.0178 1.0000 14.750 1.1494 0.06436 0.05817 0.0070 0.0177 1.0000 15.000 1.1404 0.06812 0.06219 0.0075 0.0175 1.0000 15.250 1.1284 0.07229 0.06664 0.0078 0.0174 1.0000 15.500 1.1130 0.07705 0.07169 0.0076 0.0173 1.0000 15.750 1.0968 0.08226 0.07716 0.0068 0.0173 1.0000 16.000 1.0768 0.08825 0.08343 0.0052 0.0171 1.0000 16.250 1.0566 0.09476 0.09019 0.0028 0.0171 1.0000 16.500 1.0334 0.10233 0.09801 -0.0006 0.0170 1.0000 16.750 1.0115 0.11036 0.10624 -0.0049 0.0171 1.0000 17.000 0.9856 0.11992 0.11601 -0.0106 0.0172 1.0000 17.250 0.9576 0.13101 0.12728 -0.0178 0.0173 1.0000 17.500 0.9294 0.14347 0.13988 -0.0258 0.0175 1.0000