XFOIL Version 6.96 Calculated polar for: NACA 66-021 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -1.0637 0.06950 0.06423 -0.0757 0.8242 0.0120 -19.250 -1.0617 0.06681 0.06145 -0.0763 0.8201 0.0121 -19.000 -1.0581 0.06440 0.05894 -0.0768 0.8160 0.0122 -18.750 -1.0564 0.06183 0.05628 -0.0771 0.8121 0.0122 -18.500 -1.0531 0.05944 0.05381 -0.0774 0.8090 0.0123 -18.250 -1.0468 0.05743 0.05173 -0.0775 0.8053 0.0123 -18.000 -1.0408 0.05545 0.04966 -0.0776 0.8015 0.0124 -17.750 -1.0362 0.05338 0.04751 -0.0775 0.7975 0.0124 -17.250 -1.0226 0.04977 0.04375 -0.0773 0.7911 0.0126 -17.000 -1.0141 0.04817 0.04208 -0.0771 0.7881 0.0126 -16.750 -1.0050 0.04665 0.04049 -0.0768 0.7851 0.0127 -16.500 -0.9998 0.04485 0.03863 -0.0763 0.7820 0.0130 -16.250 -0.9894 0.04353 0.03725 -0.0760 0.7789 0.0130 -16.000 -0.9827 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0.00256 0.0044 0.6973 0.6841 -1.500 -0.1764 0.00716 0.00255 0.0039 0.6967 0.6867 -1.250 -0.1471 0.00716 0.00257 0.0032 0.6961 0.6892 -1.000 -0.1177 0.00716 0.00258 0.0026 0.6955 0.6907 -0.750 -0.0883 0.00716 0.00257 0.0020 0.6949 0.6914 -0.500 -0.0589 0.00715 0.00256 0.0013 0.6943 0.6919 -0.250 -0.0294 0.00715 0.00255 0.0007 0.6937 0.6925 0.000 0.0000 0.00714 0.00255 0.0000 0.6931 0.6931 0.250 0.0294 0.00715 0.00255 -0.0007 0.6925 0.6937 0.500 0.0589 0.00715 0.00256 -0.0013 0.6919 0.6943 0.750 0.0883 0.00716 0.00257 -0.0020 0.6914 0.6949 1.000 0.1177 0.00716 0.00258 -0.0026 0.6906 0.6955 1.250 0.1471 0.00716 0.00257 -0.0032 0.6892 0.6961 1.500 0.1764 0.00716 0.00255 -0.0039 0.6867 0.6966 1.750 0.2054 0.00716 0.00256 -0.0044 0.6842 0.6972 2.000 0.2341 0.00714 0.00257 -0.0049 0.6821 0.6978 2.250 0.2629 0.00712 0.00257 -0.0054 0.6797 0.6986 2.500 0.2916 0.00710 0.00257 -0.0059 0.6764 0.6993 2.750 0.3203 0.00708 0.00255 -0.0063 0.6728 0.6999 3.000 0.3489 0.00708 0.00253 -0.0067 0.6689 0.7005 3.250 0.3766 0.00705 0.00254 -0.0070 0.6634 0.7010 3.500 0.4041 0.00703 0.00253 -0.0072 0.6557 0.7015 3.750 0.4313 0.00703 0.00253 -0.0074 0.6473 0.7019 4.000 0.4568 0.00704 0.00253 -0.0072 0.6312 0.7024 4.250 0.4659 0.00734 0.00258 -0.0037 0.5659 0.7034 4.500 0.4547 0.00804 0.00299 0.0035 0.5001 0.7047 4.750 0.4350 0.00862 0.00340 0.0124 0.4561 0.7061 5.000 0.4216 0.00949 0.00409 0.0194 0.4120 0.7073 5.250 0.4092 0.01052 0.00490 0.0259 0.3613 0.7085 5.500 0.4068 0.01138 0.00560 0.0304 0.3203 0.7097 5.750 0.4080 0.01221 0.00627 0.0342 0.2825 0.7108 6.000 0.4091 0.01308 0.00696 0.0379 0.2412 0.7119 6.250 0.4164 0.01378 0.00752 0.0405 0.2091 0.7129 6.500 0.4219 0.01458 0.00815 0.0433 0.1736 0.7140 6.750 0.4257 0.01546 0.00882 0.0463 0.1287 0.7151 7.000 0.4337 0.01623 0.00942 0.0487 0.0965 0.7161 7.250 0.4473 0.01680 0.00990 0.0502 0.0785 0.7170 7.500 0.4624 0.01732 0.01036 0.0515 0.0642 0.7179 7.750 0.4765 0.01790 0.01086 0.0529 0.0499 0.7188 8.000 0.4925 0.01842 0.01133 0.0540 0.0413 0.7195 8.250 0.5092 0.01892 0.01179 0.0550 0.0352 0.7205 8.500 0.5274 0.01934 0.01222 0.0558 0.0328 0.7219 8.750 0.5448 0.01980 0.01268 0.0566 0.0304 0.7233 9.000 0.5625 0.02026 0.01316 0.0574 0.0286 0.7249 9.250 0.5801 0.02075 0.01365 0.0582 0.0270 0.7262 9.500 0.5977 0.02124 0.01414 0.0590 0.0255 0.7276 9.750 0.6161 0.02170 0.01462 0.0597 0.0246 0.7290 10.000 0.6338 0.02221 0.01514 0.0604 0.0233 0.7303 10.250 0.6506 0.02277 0.01570 0.0611 0.0223 0.7317 10.500 0.6677 0.02332 0.01627 0.0618 0.0215 0.7331 10.750 0.6854 0.02386 0.01682 0.0625 0.0208 0.7345 11.000 0.7028 0.02442 0.01738 0.0631 0.0196 0.7357 11.250 0.7197 0.02501 0.01798 0.0637 0.0190 0.7369 11.750 0.7523 0.02628 0.01929 0.0651 0.0178 0.7399 12.000 0.7686 0.02691 0.01996 0.0658 0.0172 0.7418 12.250 0.7846 0.02757 0.02064 0.0665 0.0165 0.7437 12.500 0.8003 0.02826 0.02136 0.0671 0.0164 0.7455 12.750 0.8154 0.02901 0.02214 0.0678 0.0162 0.7475 13.000 0.8300 0.02980 0.02295 0.0685 0.0157 0.7495 13.250 0.8441 0.03064 0.02382 0.0692 0.0153 0.7513 13.500 0.8594 0.03142 0.02463 0.0697 0.0150 0.7532 13.750 0.8738 0.03226 0.02551 0.0703 0.0149 0.7548 14.000 0.8877 0.03315 0.02644 0.0709 0.0147 0.7566 14.250 0.9012 0.03406 0.02740 0.0715 0.0145 0.7591 14.500 0.9145 0.03500 0.02838 0.0721 0.0141 0.7615 14.750 0.9265 0.03605 0.02949 0.0728 0.0139 0.7640 15.000 0.9390 0.03709 0.03057 0.0733 0.0138 0.7665 15.250 0.9510 0.03819 0.03170 0.0738 0.0135 0.7690 15.500 0.9627 0.03933 0.03290 0.0743 0.0134 0.7714 15.750 0.9740 0.04053 0.03414 0.0748 0.0134 0.7736 16.000 0.9832 0.04190 0.03556 0.0753 0.0132 0.7761 16.250 0.9936 0.04320 0.03691 0.0757 0.0131 0.7791 16.500 0.9976 0.04504 0.03882 0.0764 0.0127 0.7822 16.750 1.0092 0.04630 0.04014 0.0766 0.0126 0.7853 17.000 1.0143 0.04816 0.04207 0.0770 0.0126 0.7882 17.250 1.0225 0.04979 0.04377 0.0772 0.0126 0.7912 17.750 1.0362 0.05339 0.04751 0.0775 0.0125 0.7977 18.000 1.0429 0.05527 0.04948 0.0776 0.0124 0.8018 18.250 1.0489 0.05724 0.05153 0.0775 0.0123 0.8053 18.500 1.0515 0.05961 0.05398 0.0773 0.0123 0.8091 19.000 1.0619 0.06400 0.05854 0.0767 0.0121 0.8165 19.250 1.0638 0.06660 0.06124 0.0763 0.0121 0.8206