XFOIL Version 6.96 Calculated polar for: B-29 ROOT AIRFOIL 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 -1.0541 0.08380 0.07885 -0.0590 1.0000 0.0457 -19.500 -1.0542 0.08063 0.07560 -0.0603 1.0000 0.0462 -19.250 -1.0534 0.07761 0.07250 -0.0614 1.0000 0.0466 -19.000 -1.0528 0.07464 0.06945 -0.0625 1.0000 0.0471 -18.750 -1.0550 0.07135 0.06613 -0.0637 1.0000 0.0478 -18.500 -1.0544 0.06846 0.06320 -0.0646 1.0000 0.0481 -18.250 -1.0538 0.06556 0.06025 -0.0656 1.0000 0.0488 -18.000 -1.0519 0.06284 0.05747 -0.0664 1.0000 0.0494 -17.750 -1.0487 0.06034 0.05492 -0.0671 1.0000 0.0501 -17.500 -1.0448 0.05792 0.05243 -0.0678 1.0000 0.0510 -17.250 -1.0407 0.05558 0.05002 -0.0683 1.0000 0.0515 -17.000 -1.0351 0.05342 0.04779 -0.0687 1.0000 0.0520 -16.750 -1.0314 0.05114 0.04545 -0.0691 1.0000 0.0526 -16.500 -1.0295 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0.01027 0.00327 -0.0169 0.5331 0.4488 -1.250 -0.0228 0.01007 0.00319 -0.0122 0.5207 0.4998 -1.000 -0.0018 0.01000 0.00317 -0.0108 0.5166 0.5145 -0.750 0.0208 0.00997 0.00316 -0.0098 0.5126 0.5263 -0.500 0.0422 0.00994 0.00315 -0.0084 0.5088 0.5380 -0.250 0.0642 0.00994 0.00314 -0.0072 0.5052 0.5493 0.000 0.0870 0.00990 0.00315 -0.0062 0.5016 0.5613 0.250 0.1093 0.00986 0.00315 -0.0050 0.4977 0.5731 0.500 0.1315 0.00985 0.00316 -0.0039 0.4934 0.5864 0.750 0.1523 0.00984 0.00318 -0.0024 0.4895 0.6003 1.000 0.1733 0.00984 0.00320 -0.0010 0.4861 0.6146 1.250 0.1963 0.00982 0.00323 0.0000 0.4830 0.6285 1.500 0.2178 0.00979 0.00327 0.0013 0.4793 0.6427 1.750 0.2391 0.00979 0.00330 0.0027 0.4753 0.6569 2.000 0.2602 0.00981 0.00334 0.0040 0.4715 0.6719 2.250 0.2804 0.00983 0.00339 0.0056 0.4680 0.6868 2.500 0.3026 0.00982 0.00345 0.0068 0.4650 0.7004 2.750 0.3244 0.00983 0.00351 0.0080 0.4615 0.7150 3.000 0.3452 0.00984 0.00357 0.0094 0.4576 0.7303 3.250 0.3658 0.00986 0.00364 0.0109 0.4541 0.7450 3.500 0.3861 0.00991 0.00372 0.0124 0.4507 0.7600 4.000 0.4296 0.00996 0.00391 0.0149 0.4441 0.7909 4.250 0.4519 0.01001 0.00402 0.0159 0.4405 0.8059 4.500 0.4744 0.01008 0.00414 0.0170 0.4373 0.8212 4.750 0.4959 0.01016 0.00426 0.0182 0.4339 0.8373 5.000 0.5204 0.01028 0.00442 0.0188 0.4305 0.8519 5.250 0.5491 0.01038 0.00459 0.0185 0.4273 0.8649 5.500 0.5752 0.01051 0.00477 0.0187 0.4240 0.8778 5.750 0.6077 0.01069 0.00499 0.0175 0.4207 0.8883 6.000 0.6364 0.01088 0.00519 0.0171 0.4173 0.8984 6.250 0.6683 0.01112 0.00543 0.0160 0.4137 0.9070 6.500 0.6956 0.01130 0.00564 0.0159 0.4106 0.9155 6.750 0.7333 0.01152 0.00590 0.0135 0.4071 0.9201 7.000 0.7612 0.01172 0.00614 0.0132 0.4038 0.9275 7.250 0.7893 0.01195 0.00638 0.0128 0.4003 0.9334 7.500 0.8225 0.01227 0.00667 0.0112 0.3960 0.9371 7.750 0.8490 0.01250 0.00695 0.0111 0.3914 0.9430 8.000 0.8701 0.01275 0.00723 0.0121 0.3861 0.9497 8.250 0.9006 0.01312 0.00758 0.0109 0.3804 0.9527 8.500 0.9272 0.01347 0.00795 0.0105 0.3736 0.9568 8.750 0.9406 0.01388 0.00835 0.0126 0.3644 0.9644 9.000 0.9685 0.01435 0.00880 0.0115 0.3540 0.9666 9.250 0.9944 0.01483 0.00928 0.0108 0.3460 0.9696 9.500 1.0180 0.01531 0.00976 0.0106 0.3394 0.9735 9.750 1.0351 0.01580 0.01028 0.0117 0.3333 0.9788 10.000 1.0607 0.01644 0.01091 0.0106 0.3256 0.9809 10.250 1.0862 0.01703 0.01151 0.0096 0.3164 0.9833 10.500 1.1068 0.01783 0.01230 0.0092 0.3080 0.9867 10.750 1.1258 0.01866 0.01314 0.0091 0.2982 0.9901 11.000 1.1439 0.01966 0.01412 0.0087 0.2883 0.9930 11.250 1.1616 0.02088 0.01532 0.0080 0.2766 0.9960 11.500 1.1789 0.02222 0.01663 0.0071 0.2631 0.9985 11.750 1.1889 0.02377 0.01815 0.0072 0.2490 1.0000 12.000 1.1794 0.02534 0.01969 0.0108 0.2369 1.0000 12.250 1.1691 0.02711 0.02143 0.0142 0.2244 1.0000 12.500 1.1580 0.02907 0.02334 0.0175 0.2114 1.0000 12.750 1.1464 0.03123 0.02545 0.0204 0.1980 1.0000 13.000 1.1342 0.03358 0.02776 0.0231 0.1850 1.0000 13.250 1.1250 0.03591 0.03005 0.0253 0.1738 1.0000 13.500 1.1177 0.03822 0.03234 0.0273 0.1638 1.0000 13.750 1.1114 0.04056 0.03466 0.0289 0.1555 1.0000 14.000 1.1055 0.04298 0.03708 0.0304 0.1474 1.0000 14.250 1.1019 0.04530 0.03940 0.0316 0.1399 1.0000 14.500 1.0976 0.04775 0.04184 0.0328 0.1332 1.0000 14.750 1.0948 0.05015 0.04424 0.0337 0.1257 1.0000 15.000 1.0918 0.05263 0.04673 0.0345 0.1203 1.0000 15.250 1.0894 0.05513 0.04922 0.0352 0.1129 1.0000 15.500 1.0864 0.05773 0.05182 0.0358 0.1076 1.0000 15.750 1.0848 0.06024 0.05433 0.0363 0.1019 1.0000 16.000 1.0818 0.06297 0.05707 0.0367 0.0964 1.0000 16.250 1.0797 0.06563 0.05972 0.0371 0.0914 1.0000 16.500 1.0789 0.06822 0.06234 0.0373 0.0875 1.0000 16.750 1.0780 0.07083 0.06495 0.0375 0.0834 1.0000 17.000 1.0773 0.07349 0.06763 0.0376 0.0804 1.0000 17.250 1.0785 0.07596 0.07012 0.0376 0.0775 1.0000 17.500 1.0776 0.07871 0.07290 0.0376 0.0751 1.0000 17.750 1.0793 0.08118 0.07540 0.0375 0.0730 1.0000 18.000 1.0813 0.08364 0.07789 0.0374 0.0709 1.0000 18.250 1.0813 0.08638 0.08066 0.0371 0.0688 1.0000 18.500 1.0813 0.08914 0.08343 0.0369 0.0669 1.0000