XFOIL Version 6.96 Calculated polar for: NACA 63 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 -1.0901 0.08701 0.08322 -0.0531 1.0000 0.0142 -19.500 -1.0992 0.08229 0.07840 -0.0553 1.0000 0.0142 -19.250 -1.1022 0.07855 0.07458 -0.0570 1.0000 0.0145 -19.000 -1.1099 0.07419 0.07013 -0.0590 1.0000 0.0145 -18.750 -1.1139 0.07038 0.06625 -0.0606 1.0000 0.0146 -18.500 -1.1198 0.06645 0.06223 -0.0623 1.0000 0.0147 -18.250 -1.1237 0.06280 0.05853 -0.0638 1.0000 0.0150 -18.000 -1.1260 0.05945 0.05511 -0.0651 1.0000 0.0152 -17.750 -1.1261 0.05643 0.05201 -0.0662 1.0000 0.0152 -17.500 -1.1258 0.05353 0.04905 -0.0672 1.0000 0.0153 -17.250 -1.1211 0.05116 0.04665 -0.0680 1.0000 0.0159 -17.000 -1.1182 0.04863 0.04407 -0.0687 1.0000 0.0161 -16.750 -1.1166 0.04604 0.04140 -0.0694 1.0000 0.0161 -16.500 -1.1091 0.04412 0.03944 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0.6680 0.0639 -6.750 -0.4320 0.01077 0.00419 -0.0672 0.6626 0.0712 -6.500 -0.4050 0.01053 0.00396 -0.0673 0.6568 0.0793 -6.000 -0.3506 0.01003 0.00352 -0.0676 0.6465 0.1026 -5.750 -0.3232 0.00977 0.00331 -0.0678 0.6409 0.1183 -5.500 -0.2957 0.00952 0.00310 -0.0680 0.6354 0.1377 -5.250 -0.2682 0.00922 0.00289 -0.0683 0.6310 0.1614 -5.000 -0.2404 0.00889 0.00268 -0.0686 0.6263 0.1910 -4.750 -0.2126 0.00857 0.00247 -0.0689 0.6210 0.2255 -4.250 -0.1566 0.00790 0.00208 -0.0697 0.6114 0.3066 -4.000 -0.1280 0.00763 0.00194 -0.0701 0.6067 0.3446 -3.750 -0.0992 0.00743 0.00183 -0.0705 0.6020 0.3787 -3.500 -0.0701 0.00733 0.00176 -0.0708 0.5977 0.4021 -3.250 -0.0406 0.00724 0.00171 -0.0712 0.5935 0.4193 -3.000 -0.0111 0.00717 0.00166 -0.0716 0.5887 0.4352 -2.750 0.0182 0.00712 0.00163 -0.0719 0.5836 0.4488 -2.500 0.0476 0.00709 0.00160 -0.0723 0.5795 0.4603 -2.250 0.0773 0.00707 0.00158 -0.0727 0.5756 0.4708 -2.000 0.1069 0.00703 0.00157 -0.0730 0.5713 0.4801 -1.750 0.1364 0.00704 0.00156 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3.250 0.7212 0.00772 0.00225 -0.0794 0.4755 0.5843 3.500 0.7499 0.00778 0.00233 -0.0796 0.4690 0.5891 3.750 0.7778 0.00791 0.00243 -0.0797 0.4605 0.5940 4.000 0.8061 0.00799 0.00253 -0.0799 0.4516 0.5988 4.250 0.8338 0.00811 0.00264 -0.0799 0.4435 0.6041 4.500 0.8620 0.00820 0.00275 -0.0801 0.4355 0.6091 4.750 0.8891 0.00836 0.00288 -0.0800 0.4247 0.6135 5.000 0.9153 0.00856 0.00304 -0.0799 0.4066 0.6182 5.250 0.9402 0.00884 0.00324 -0.0795 0.3818 0.6238 5.500 0.9649 0.00915 0.00346 -0.0791 0.3598 0.6292 5.750 0.9891 0.00946 0.00369 -0.0787 0.3369 0.6339 6.000 1.0118 0.00986 0.00399 -0.0780 0.3117 0.6389 6.250 1.0329 0.01034 0.00434 -0.0771 0.2818 0.6441 6.500 1.0517 0.01094 0.00477 -0.0758 0.2472 0.6492 6.750 1.0696 0.01153 0.00521 -0.0745 0.2150 0.6542 7.000 1.0880 0.01206 0.00563 -0.0731 0.1890 0.6600 7.250 1.1049 0.01261 0.00608 -0.0716 0.1652 0.6654 7.500 1.1218 0.01313 0.00651 -0.0700 0.1462 0.6701 7.750 1.1369 0.01363 0.00695 -0.0681 0.1297 0.6755 8.000 1.1472 0.01413 0.00740 -0.0653 0.1147 0.6818 8.250 1.1573 0.01471 0.00792 -0.0626 0.1014 0.6872 8.500 1.1682 0.01528 0.00848 -0.0602 0.0906 0.6930 8.750 1.1792 0.01590 0.00907 -0.0579 0.0811 0.6990 9.000 1.1903 0.01656 0.00972 -0.0558 0.0732 0.7050 9.250 1.2003 0.01730 0.01046 -0.0537 0.0656 0.7111 9.750 1.2233 0.01882 0.01200 -0.0503 0.0556 0.7242 10.000 1.2339 0.01968 0.01288 -0.0486 0.0514 0.7308 10.250 1.2461 0.02051 0.01374 -0.0472 0.0481 0.7383 10.500 1.2562 0.02149 0.01474 -0.0457 0.0446 0.7453 10.750 1.2684 0.02239 0.01568 -0.0444 0.0422 0.7531 11.000 1.2788 0.02344 0.01676 -0.0431 0.0397 0.7607 11.250 1.2897 0.02447 0.01784 -0.0419 0.0378 0.7695 11.500 1.3005 0.02556 0.01898 -0.0408 0.0357 0.7786 11.750 1.3100 0.02676 0.02022 -0.0397 0.0338 0.7881 12.000 1.3201 0.02795 0.02147 -0.0386 0.0321 0.7980 12.250 1.3295 0.02920 0.02279 -0.0376 0.0306 0.8105 12.500 1.3377 0.03058 0.02422 -0.0366 0.0291 0.8237 12.750 1.3466 0.03190 0.02564 -0.0357 0.0281 0.8402 13.000 1.3545 0.03328 0.02712 -0.0346 0.0270 0.8620 13.250 1.3600 0.03466 0.02864 -0.0332 0.0259 0.9040 14.250 1.3949 0.04145 0.03567 -0.0321 0.0223 1.0000 14.500 1.4022 0.04335 0.03761 -0.0318 0.0217 1.0000 14.750 1.4079 0.04543 0.03973 -0.0315 0.0210 1.0000 15.000 1.4158 0.04736 0.04170 -0.0314 0.0206 1.0000 15.250 1.4228 0.04940 0.04380 -0.0313 0.0201 1.0000 15.500 1.4288 0.05161 0.04605 -0.0313 0.0196 1.0000 15.750 1.4350 0.05381 0.04830 -0.0313 0.0191 1.0000 16.000 1.4395 0.05626 0.05079 -0.0315 0.0186 1.0000 16.250 1.4438 0.05877 0.05334 -0.0317 0.0180 1.0000 16.500 1.4479 0.06136 0.05598 -0.0320 0.0177 1.0000 16.750 1.4532 0.06386 0.05855 -0.0323 0.0173 1.0000 17.000 1.4578 0.06645 0.06121 -0.0327 0.0170 1.0000 17.250 1.4615 0.06924 0.06405 -0.0333 0.0166 1.0000 17.500 1.4654 0.07201 0.06688 -0.0338 0.0162 1.0000 17.750 1.4674 0.07509 0.07003 -0.0345 0.0160 1.0000 18.000 1.4698 0.07815 0.07314 -0.0353 0.0156 1.0000 18.250 1.4705 0.08149 0.07653 -0.0362 0.0153 1.0000 18.500 1.4706 0.08498 0.08009 -0.0372 0.0150 1.0000