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 = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.6930 0.08621 0.07839 -0.0455 1.0000 0.0617 -12.500 -0.7193 0.07934 0.07138 -0.0494 1.0000 0.0615 -12.250 -0.7432 0.07354 0.06542 -0.0523 1.0000 0.0614 -12.000 -0.7642 0.06867 0.06035 -0.0541 1.0000 0.0615 -11.750 -0.7837 0.06439 0.05584 -0.0549 1.0000 0.0616 -11.500 -0.7997 0.06073 0.05190 -0.0548 1.0000 0.0619 -11.250 -0.7992 0.05774 0.04883 -0.0543 1.0000 0.0627 -11.000 -0.7966 0.05518 0.04616 -0.0535 1.0000 0.0638 -10.750 -0.7942 0.05289 0.04376 -0.0525 1.0000 0.0653 -10.500 -0.7906 0.05066 0.04137 -0.0513 1.0000 0.0672 -10.250 -0.7856 0.04831 0.03877 -0.0502 1.0000 0.0693 -10.000 -0.7779 0.04595 0.03607 -0.0489 1.0000 0.0713 -9.750 -0.7630 0.04375 0.03366 -0.0481 1.0000 0.0735 -9.500 -0.7446 0.04212 0.03205 -0.0474 1.0000 0.0768 -9.250 -0.7278 0.04054 0.03034 -0.0464 1.0000 0.0806 -9.000 -0.7071 0.03896 0.02847 -0.0455 1.0000 0.0844 -8.750 -0.6857 0.03764 0.02730 -0.0447 1.0000 0.0889 -8.500 -0.6684 0.03651 0.02610 -0.0433 1.0000 0.0944 -8.250 -0.6520 0.03543 0.02496 -0.0416 1.0000 0.0998 -8.000 -0.6443 0.03449 0.02410 -0.0391 1.0000 0.1050 -7.750 -0.6401 0.03370 0.02323 -0.0360 1.0000 0.1113 -7.500 -0.6431 0.03288 0.02254 -0.0323 1.0000 0.1167 -7.250 -0.6459 0.03215 0.02181 -0.0284 1.0000 0.1236 -7.000 -0.6494 0.03133 0.02105 -0.0247 1.0000 0.1306 -6.750 -0.6347 0.03003 0.01984 -0.0245 0.9930 0.1476 -6.500 -0.6111 0.02825 0.01833 -0.0263 0.9814 0.1833 -6.250 -0.5904 0.02636 0.01700 -0.0279 0.9701 0.2524 -6.000 -0.5671 0.02534 0.01677 -0.0285 0.9599 0.3647 -5.750 -0.5397 0.02544 0.01705 -0.0285 0.9497 0.4457 -5.500 -0.5078 0.02590 0.01746 -0.0288 0.9411 0.4983 -5.250 -0.4761 0.02644 0.01784 -0.0291 0.9322 0.5385 -5.000 -0.4441 0.02733 0.01865 -0.0284 0.9240 0.5660 -4.750 -0.4121 0.02779 0.01894 -0.0285 0.9160 0.5896 -4.500 -0.3825 0.02826 0.01925 -0.0279 0.9073 0.6071 -4.250 -0.3504 0.02855 0.01939 -0.0281 0.8998 0.6233 -4.000 -0.3239 0.02869 0.01938 -0.0275 0.8908 0.6371 -3.750 -0.2905 0.02890 0.01944 -0.0278 0.8836 0.6470 -3.500 -0.2669 0.02878 0.01917 -0.0273 0.8743 0.6583 -3.250 -0.2371 0.02869 0.01894 -0.0277 0.8669 0.6685 -3.000 -0.2134 0.02866 0.01879 -0.0270 0.8578 0.6772 -2.750 -0.1869 0.02841 0.01839 -0.0273 0.8503 0.6882 -2.500 -0.1627 0.02848 0.01839 -0.0264 0.8416 0.6951 -2.250 -0.1376 0.02821 0.01798 -0.0266 0.8340 0.7058 -2.000 -0.1131 0.02829 0.01801 -0.0258 0.8258 0.7122 -1.750 -0.0891 0.02808 0.01768 -0.0258 0.8181 0.7225 -1.500 -0.0632 0.02812 0.01767 -0.0252 0.8107 0.7287 -1.250 -0.0408 0.02801 0.01747 -0.0249 0.8025 0.7383 -1.000 -0.0121 0.02797 0.01739 -0.0248 0.7966 0.7450 -0.750 0.0065 0.02798 0.01735 -0.0239 0.7873 0.7543 -0.500 0.0365 0.02790 0.01723 -0.0241 0.7820 0.7613 -0.250 0.0538 0.02800 0.01731 -0.0230 0.7726 0.7705 0.000 0.0813 0.02797 0.01725 -0.0228 0.7666 0.7781 0.250 0.1004 0.02807 0.01734 -0.0219 0.7584 0.7875 0.500 0.1251 0.02811 0.01738 -0.0214 0.7516 0.7953 0.750 0.1498 0.02812 0.01737 -0.0211 0.7455 0.8050 1.000 0.1689 0.02832 0.01762 -0.0200 0.7369 0.8132 1.250 0.1967 0.02826 0.01755 -0.0201 0.7319 0.8232 1.500 0.2132 0.02858 0.01793 -0.0187 0.7228 0.8322 1.750 0.2394 0.02860 0.01797 -0.0184 0.7169 0.8419 2.000 0.2595 0.02883 0.01825 -0.0176 0.7094 0.8524 2.250 0.2828 0.02899 0.01847 -0.0171 0.7021 0.8624 2.500 0.3137 0.02891 0.01843 -0.0173 0.6976 0.8728 2.750 0.3275 0.02941 0.01903 -0.0160 0.6874 0.8852 3.000 0.3610 0.02936 0.01906 -0.0167 0.6823 0.8952 3.250 0.3798 0.02984 0.01965 -0.0162 0.6728 0.9083 3.500 0.4133 0.02984 0.01973 -0.0172 0.6668 0.9201 3.750 0.4397 0.03027 0.02030 -0.0180 0.6579 0.9338 4.000 0.4794 0.03033 0.02048 -0.0202 0.6510 0.9447 4.250 0.5147 0.03070 0.02102 -0.0225 0.6421 0.9575 4.500 0.5578 0.03072 0.02119 -0.0254 0.6345 0.9688 4.750 0.5948 0.03112 0.02176 -0.0281 0.6241 0.9834 5.000 0.6422 0.03079 0.02161 -0.0311 0.6165 0.9960 5.250 0.6388 0.03143 0.02231 -0.0275 0.6046 1.0000 5.500 0.6554 0.03143 0.02237 -0.0257 0.5950 1.0000 5.750 0.6785 0.03125 0.02230 -0.0247 0.5844 1.0000 6.000 0.6947 0.03150 0.02263 -0.0232 0.5709 1.0000 6.250 0.7168 0.03146 0.02270 -0.0222 0.5572 1.0000 6.500 0.7421 0.03118 0.02254 -0.0213 0.5427 1.0000 6.750 0.7671 0.03079 0.02228 -0.0201 0.5258 1.0000 7.000 0.7923 0.03020 0.02180 -0.0188 0.5059 1.0000 7.250 0.8140 0.02972 0.02139 -0.0170 0.4822 1.0000 7.500 0.8326 0.02937 0.02110 -0.0150 0.4536 1.0000 7.750 0.8438 0.02959 0.02135 -0.0128 0.4197 1.0000 8.000 0.8529 0.02995 0.02166 -0.0103 0.3790 1.0000 8.250 0.8612 0.03043 0.02190 -0.0077 0.3294 1.0000 8.500 0.8644 0.03160 0.02269 -0.0053 0.2772 1.0000 8.750 0.8631 0.03344 0.02414 -0.0032 0.2330 1.0000 9.000 0.8614 0.03561 0.02602 -0.0017 0.1984 1.0000 9.250 0.8600 0.03797 0.02810 -0.0005 0.1719 1.0000 9.500 0.8620 0.04023 0.03022 0.0005 0.1512 1.0000 9.750 0.8652 0.04247 0.03233 0.0013 0.1352 1.0000 10.000 0.8708 0.04460 0.03438 0.0021 0.1226 1.0000 10.250 0.8783 0.04661 0.03629 0.0028 0.1133 1.0000 10.500 0.8898 0.04841 0.03815 0.0035 0.1042 1.0000 10.750 0.9028 0.05013 0.03987 0.0042 0.0971 1.0000 11.000 0.9184 0.05174 0.04153 0.0049 0.0907 1.0000 11.250 0.9368 0.05327 0.04309 0.0056 0.0852 1.0000 11.500 0.9545 0.05497 0.04499 0.0062 0.0800 1.0000 11.750 0.9785 0.05632 0.04625 0.0068 0.0757 1.0000 12.000 0.9923 0.05867 0.04893 0.0072 0.0722 1.0000 12.250 1.0034 0.06111 0.05159 0.0075 0.0690 1.0000 12.500 1.0154 0.06344 0.05400 0.0077 0.0663 1.0000 12.750 1.0299 0.06591 0.05653 0.0079 0.0641 1.0000 13.000 1.0243 0.06982 0.06083 0.0076 0.0627 1.0000 13.250 1.0165 0.07408 0.06541 0.0069 0.0615 1.0000 13.500 1.0059 0.07873 0.07035 0.0058 0.0604 1.0000 13.750 0.9923 0.08391 0.07579 0.0041 0.0596 1.0000 14.000 0.9741 0.09001 0.08214 0.0016 0.0593 1.0000 14.250 0.9488 0.09752 0.08991 -0.0022 0.0592 1.0000 14.500 0.9130 0.10770 0.10033 -0.0082 0.0599 1.0000 14.750 0.8686 0.12149 0.11433 -0.0169 0.0610 1.0000