XFOIL Version 6.96 Calculated polar for: NACA 64(4)-421 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9590 0.09120 0.08641 -0.0639 1.0000 0.0248 -19.500 -0.9599 0.08776 0.08288 -0.0654 1.0000 0.0251 -19.250 -0.9590 0.08461 0.07964 -0.0667 1.0000 0.0253 -19.000 -0.9584 0.08151 0.07648 -0.0679 1.0000 0.0255 -18.750 -0.9583 0.07841 0.07333 -0.0690 1.0000 0.0258 -18.500 -0.9572 0.07548 0.07036 -0.0700 1.0000 0.0260 -18.250 -0.9556 0.07261 0.06745 -0.0710 1.0000 0.0263 -18.000 -0.9523 0.07002 0.06480 -0.0719 1.0000 0.0265 -17.750 -0.9492 0.06741 0.06214 -0.0727 1.0000 0.0268 -17.500 -0.9451 0.06501 0.05969 -0.0733 1.0000 0.0271 -17.250 -0.9410 0.06262 0.05725 -0.0740 1.0000 0.0274 -17.000 -0.9353 0.06045 0.05503 -0.0745 1.0000 0.0277 -16.750 -0.9295 0.05831 0.05284 -0.0749 1.0000 0.0281 -16.500 -0.9230 0.05630 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0.00303 -0.0685 0.5627 0.5251 -1.500 0.1496 0.00972 0.00301 -0.0689 0.5597 0.5273 -1.250 0.1788 0.00973 0.00299 -0.0693 0.5566 0.5290 -1.000 0.2077 0.00973 0.00297 -0.0696 0.5535 0.5309 -0.750 0.2366 0.00975 0.00298 -0.0699 0.5506 0.5327 -0.500 0.2656 0.00978 0.00299 -0.0703 0.5482 0.5347 -0.250 0.2950 0.00978 0.00301 -0.0707 0.5460 0.5368 0.000 0.3243 0.00980 0.00303 -0.0711 0.5437 0.5392 0.250 0.3535 0.00983 0.00306 -0.0714 0.5413 0.5417 0.500 0.3827 0.00986 0.00309 -0.0718 0.5390 0.5440 0.750 0.4118 0.00991 0.00312 -0.0722 0.5368 0.5460 1.250 0.4695 0.01000 0.00320 -0.0728 0.5327 0.5504 1.500 0.4983 0.01006 0.00327 -0.0731 0.5307 0.5529 1.750 0.5274 0.01010 0.00334 -0.0735 0.5290 0.5555 2.000 0.5564 0.01013 0.00341 -0.0739 0.5271 0.5583 2.250 0.5854 0.01018 0.00349 -0.0742 0.5250 0.5612 2.500 0.6143 0.01024 0.00357 -0.0746 0.5231 0.5641 2.750 0.6431 0.01031 0.00365 -0.0749 0.5212 0.5669 3.000 0.6716 0.01036 0.00374 -0.0752 0.5188 0.5698 3.250 0.6999 0.01043 0.00383 -0.0754 0.5161 0.5731 3.500 0.7280 0.01052 0.00392 -0.0756 0.5133 0.5765 3.750 0.7564 0.01061 0.00404 -0.0759 0.5113 0.5803 4.000 0.7849 0.01067 0.00416 -0.0762 0.5094 0.5843 4.250 0.8133 0.01075 0.00429 -0.0765 0.5073 0.5879 4.500 0.8413 0.01081 0.00442 -0.0767 0.5051 0.5919 4.750 0.8693 0.01089 0.00455 -0.0769 0.5027 0.5961 5.000 0.8966 0.01098 0.00467 -0.0769 0.4992 0.6004 5.250 0.9230 0.01111 0.00478 -0.0768 0.4941 0.6047 5.500 0.9495 0.01115 0.00491 -0.0768 0.4888 0.6087 5.750 0.9753 0.01122 0.00504 -0.0766 0.4826 0.6132 6.000 0.9995 0.01135 0.00516 -0.0761 0.4751 0.6180 6.250 1.0249 0.01143 0.00531 -0.0758 0.4678 0.6230 6.500 1.0495 0.01157 0.00547 -0.0754 0.4619 0.6276 6.750 1.0739 0.01170 0.00565 -0.0750 0.4563 0.6325 7.000 1.0976 0.01182 0.00585 -0.0745 0.4478 0.6379 7.250 1.1184 0.01200 0.00604 -0.0734 0.4353 0.6434 7.750 1.1372 0.01271 0.00661 -0.0674 0.3819 0.6537 8.000 1.1339 0.01353 0.00729 -0.0626 0.3514 0.6595 8.250 1.1316 0.01451 0.00815 -0.0583 0.3243 0.6653 8.500 1.1311 0.01555 0.00910 -0.0547 0.2984 0.6707 8.750 1.1276 0.01683 0.01029 -0.0509 0.2721 0.6771 9.000 1.1245 0.01824 0.01162 -0.0476 0.2467 0.6837 9.250 1.1228 0.01972 0.01302 -0.0447 0.2258 0.6900 9.500 1.1218 0.02126 0.01452 -0.0421 0.2060 0.6965 9.750 1.1216 0.02287 0.01608 -0.0398 0.1878 0.7037 10.250 1.1239 0.02618 0.01934 -0.0360 0.1573 0.7168 10.500 1.1243 0.02799 0.02113 -0.0343 0.1424 0.7238 11.000 1.1282 0.03162 0.02473 -0.0315 0.1185 0.7374 11.250 1.1316 0.03342 0.02653 -0.0303 0.1090 0.7450 11.500 1.1354 0.03529 0.02839 -0.0293 0.0998 0.7520 11.750 1.1400 0.03710 0.03023 -0.0284 0.0915 0.7597 12.000 1.1444 0.03901 0.03214 -0.0276 0.0834 0.7678 12.250 1.1486 0.04098 0.03413 -0.0269 0.0762 0.7755 12.750 1.1596 0.04481 0.03801 -0.0258 0.0642 0.7932 13.000 1.1658 0.04670 0.03994 -0.0253 0.0586 0.8038 13.250 1.1719 0.04866 0.04194 -0.0249 0.0547 0.8139 13.500 1.1782 0.05060 0.04393 -0.0245 0.0505 0.8258 13.750 1.1844 0.05256 0.04595 -0.0242 0.0468 0.8387 14.000 1.1903 0.05453 0.04798 -0.0238 0.0441 0.8537 14.250 1.1959 0.05641 0.04996 -0.0232 0.0413 0.8747 14.500 1.2000 0.05838 0.05205 -0.0226 0.0389 0.9144 15.000 1.2162 0.06273 0.05650 -0.0235 0.0347 1.0000 15.250 1.2242 0.06486 0.05867 -0.0238 0.0331 1.0000 15.500 1.2314 0.06709 0.06093 -0.0241 0.0317 1.0000 16.000 1.2445 0.07183 0.06574 -0.0248 0.0293 1.0000 16.250 1.2510 0.07425 0.06820 -0.0252 0.0282 1.0000 16.500 1.2563 0.07685 0.07084 -0.0257 0.0272 1.0000 16.750 1.2619 0.07941 0.07343 -0.0263 0.0264 1.0000 17.000 1.2677 0.08199 0.07608 -0.0269 0.0256 1.0000 17.250 1.2734 0.08463 0.07877 -0.0275 0.0248 1.0000 17.500 1.2783 0.08736 0.08155 -0.0282 0.0240 1.0000 17.750 1.2815 0.09039 0.08463 -0.0291 0.0234 1.0000 18.000 1.2857 0.09329 0.08758 -0.0299 0.0228 1.0000 18.250 1.2901 0.09619 0.09055 -0.0308 0.0223 1.0000 18.500 1.2938 0.09922 0.09365 -0.0318 0.0217 1.0000 18.750 1.2976 0.10225 0.09674 -0.0329 0.0211 1.0000 19.000 1.2993 0.10563 0.10017 -0.0341 0.0206 1.0000 19.250 1.3009 0.10903 0.10363 -0.0354 0.0201 1.0000