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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0946 0.07661 0.07229 -0.0649 1.0000 0.0205 -19.500 -1.0934 0.07371 0.06932 -0.0660 1.0000 0.0208 -19.250 -1.0917 0.07086 0.06642 -0.0670 1.0000 0.0210 -19.000 -1.0888 0.06821 0.06371 -0.0678 1.0000 0.0211 -18.750 -1.0860 0.06561 0.06105 -0.0686 1.0000 0.0213 -18.500 -1.0813 0.06325 0.05864 -0.0693 1.0000 0.0216 -18.250 -1.0775 0.06081 0.05613 -0.0700 1.0000 0.0217 -18.000 -1.0706 0.05876 0.05404 -0.0705 1.0000 0.0219 -17.750 -1.0665 0.05640 0.05163 -0.0711 1.0000 0.0221 -17.500 -1.0623 0.05414 0.04933 -0.0716 1.0000 0.0224 -17.250 -1.0576 0.05193 0.04709 -0.0720 1.0000 0.0227 -17.000 -1.0508 0.04999 0.04511 -0.0724 1.0000 0.0229 -16.750 -1.0437 0.04809 0.04317 -0.0726 1.0000 0.0231 -16.500 -1.0249 0.04594 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-0.0708 0.5301 0.5017 -1.250 0.1875 0.00774 0.00202 -0.0712 0.5281 0.5043 -1.000 0.2174 0.00775 0.00202 -0.0717 0.5260 0.5062 -0.750 0.2471 0.00777 0.00202 -0.0721 0.5238 0.5076 -0.500 0.2768 0.00779 0.00203 -0.0726 0.5214 0.5088 -0.250 0.3063 0.00781 0.00204 -0.0730 0.5191 0.5103 0.000 0.3357 0.00783 0.00206 -0.0734 0.5169 0.5126 0.250 0.3649 0.00786 0.00208 -0.0738 0.5146 0.5149 0.500 0.3941 0.00790 0.00212 -0.0742 0.5123 0.5172 0.750 0.4238 0.00791 0.00215 -0.0746 0.5110 0.5194 1.000 0.4535 0.00793 0.00218 -0.0751 0.5095 0.5215 1.250 0.4831 0.00796 0.00222 -0.0755 0.5079 0.5236 1.500 0.5125 0.00799 0.00226 -0.0759 0.5063 0.5256 1.750 0.5419 0.00803 0.00230 -0.0763 0.5044 0.5274 2.000 0.5711 0.00807 0.00235 -0.0767 0.5022 0.5295 2.250 0.6001 0.00811 0.00240 -0.0770 0.5000 0.5323 2.500 0.6289 0.00816 0.00247 -0.0774 0.4975 0.5351 2.750 0.6574 0.00824 0.00254 -0.0776 0.4946 0.5380 3.000 0.6866 0.00827 0.00261 -0.0780 0.4928 0.5409 3.250 0.7159 0.00831 0.00267 -0.0784 0.4911 0.5437 3.500 0.7450 0.00836 0.00275 -0.0788 0.4894 0.5463 3.750 0.7739 0.00841 0.00282 -0.0791 0.4875 0.5490 4.000 0.8027 0.00846 0.00291 -0.0794 0.4854 0.5525 4.250 0.8309 0.00852 0.00299 -0.0797 0.4820 0.5562 4.500 0.8577 0.00864 0.00310 -0.0796 0.4764 0.5598 4.750 0.8866 0.00867 0.00318 -0.0800 0.4721 0.5634 5.000 0.9146 0.00875 0.00327 -0.0802 0.4669 0.5668 5.250 0.9404 0.00889 0.00338 -0.0800 0.4586 0.5710 5.500 0.9685 0.00893 0.00348 -0.0802 0.4517 0.5756 5.750 0.9954 0.00904 0.00360 -0.0802 0.4457 0.5800 6.000 1.0216 0.00916 0.00373 -0.0801 0.4391 0.5840 6.250 1.0471 0.00931 0.00387 -0.0799 0.4267 0.5875 6.500 1.0685 0.00959 0.00408 -0.0790 0.4008 0.5922 6.750 1.0781 0.01030 0.00455 -0.0761 0.3534 0.5968 7.000 1.0858 0.01102 0.00508 -0.0730 0.3155 0.6013 7.250 1.0881 0.01166 0.00558 -0.0687 0.2844 0.6053 7.500 1.0908 0.01240 0.00620 -0.0648 0.2571 0.6094 7.750 1.0949 0.01315 0.00686 -0.0613 0.2327 0.6145 8.000 1.0993 0.01395 0.00758 -0.0581 0.2120 0.6197 8.250 1.1039 0.01482 0.00839 -0.0552 0.1937 0.6246 8.500 1.1092 0.01574 0.00925 -0.0525 0.1769 0.6292 8.750 1.1134 0.01677 0.01023 -0.0499 0.1595 0.6348 9.000 1.1180 0.01787 0.01129 -0.0475 0.1441 0.6406 9.250 1.1236 0.01900 0.01238 -0.0454 0.1313 0.6459 9.500 1.1291 0.02020 0.01356 -0.0434 0.1194 0.6512 9.750 1.1333 0.02153 0.01486 -0.0415 0.1072 0.6574 10.000 1.1391 0.02284 0.01615 -0.0398 0.0979 0.6636 10.500 1.1516 0.02555 0.01885 -0.0369 0.0811 0.6752 10.750 1.1567 0.02705 0.02035 -0.0355 0.0731 0.6819 11.000 1.1636 0.02848 0.02178 -0.0343 0.0672 0.6881 11.250 1.1697 0.03001 0.02332 -0.0331 0.0609 0.6946 11.500 1.1749 0.03167 0.02499 -0.0321 0.0545 0.7022 11.750 1.1830 0.03316 0.02650 -0.0312 0.0504 0.7088 12.000 1.1909 0.03470 0.02807 -0.0304 0.0469 0.7155 12.250 1.1983 0.03632 0.02972 -0.0297 0.0432 0.7230 12.500 1.2058 0.03799 0.03141 -0.0291 0.0399 0.7296 12.750 1.2145 0.03958 0.03305 -0.0285 0.0375 0.7366 13.000 1.2218 0.04133 0.03483 -0.0280 0.0349 0.7443 13.500 1.2388 0.04473 0.03831 -0.0272 0.0313 0.7589 13.750 1.2475 0.04644 0.04007 -0.0269 0.0297 0.7671 14.000 1.2557 0.04824 0.04192 -0.0267 0.0286 0.7748 14.250 1.2639 0.05005 0.04378 -0.0264 0.0273 0.7837 14.500 1.2719 0.05192 0.04570 -0.0263 0.0263 0.7927 14.750 1.2804 0.05377 0.04762 -0.0262 0.0253 0.8034 15.000 1.2891 0.05559 0.04951 -0.0261 0.0243 0.8153 15.250 1.2956 0.05767 0.05165 -0.0260 0.0235 0.8286 15.500 1.3032 0.05960 0.05367 -0.0259 0.0229 0.8450 15.750 1.3109 0.06144 0.05563 -0.0257 0.0222 0.8679 16.000 1.3146 0.06335 0.05773 -0.0250 0.0215 0.9186 16.500 1.3312 0.06780 0.06231 -0.0262 0.0200 1.0000 16.750 1.3384 0.07006 0.06461 -0.0265 0.0196 1.0000 17.000 1.3465 0.07222 0.06680 -0.0269 0.0190 1.0000 17.250 1.3529 0.07463 0.06926 -0.0274 0.0185 1.0000 17.500 1.3589 0.07711 0.07178 -0.0279 0.0178 1.0000 17.750 1.3650 0.07957 0.07427 -0.0284 0.0174 1.0000 18.000 1.3694 0.08231 0.07705 -0.0290 0.0169 1.0000 18.250 1.3756 0.08482 0.07961 -0.0297 0.0165 1.0000 18.500 1.3819 0.08734 0.08218 -0.0303 0.0160 1.0000 18.750 1.3857 0.09024 0.08514 -0.0312 0.0156 1.0000 19.000 1.3903 0.09304 0.08797 -0.0320 0.0151 1.0000 19.250 1.3938 0.09600 0.09098 -0.0329 0.0147 1.0000