XFOIL Version 6.96 Calculated polar for: P-51D TIP (BL215) 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.5626 0.14396 0.14152 -0.0031 0.7670 0.0028 -12.750 -0.9697 0.04115 0.03825 -0.0504 0.7663 0.0023 -12.250 -1.0066 0.03415 0.03077 -0.0447 0.7606 0.0023 -12.000 -1.0123 0.03177 0.02818 -0.0417 0.7580 0.0023 -11.750 -1.0083 0.02961 0.02580 -0.0398 0.7557 0.0024 -11.500 -0.9980 0.02797 0.02399 -0.0384 0.7534 0.0025 -11.250 -0.9853 0.02646 0.02229 -0.0372 0.7513 0.0025 -10.750 -0.9543 0.02371 0.01920 -0.0353 0.7475 0.0027 -10.500 -0.9374 0.02229 0.01758 -0.0344 0.7455 0.0028 -10.250 -0.9181 0.02119 0.01632 -0.0337 0.7434 0.0029 -10.000 -0.8975 0.02023 0.01522 -0.0331 0.7413 0.0030 -9.750 -0.8773 0.01910 0.01391 -0.0325 0.7393 0.0031 -9.500 -0.8554 0.01826 0.01290 -0.0320 0.7374 0.0033 -9.250 -0.8328 0.01749 0.01201 -0.0316 0.7357 0.0034 -9.000 -0.8099 0.01673 0.01113 -0.0312 0.7342 0.0035 -8.750 -0.7863 0.01607 0.01036 -0.0309 0.7326 0.0036 -8.500 -0.7623 0.01546 0.00966 -0.0306 0.7309 0.0037 -8.250 -0.7398 0.01456 0.00861 -0.0301 0.7292 0.0040 -8.000 -0.7161 0.01388 0.00782 -0.0297 0.7275 0.0044 -7.750 -0.6917 0.01335 0.00722 -0.0294 0.7258 0.0048 -7.500 -0.6666 0.01294 0.00677 -0.0293 0.7241 0.0054 -7.250 -0.6412 0.01256 0.00630 -0.0291 0.7224 0.0060 -7.000 -0.6156 0.01221 0.00588 -0.0290 0.7209 0.0065 -6.750 -0.5898 0.01185 0.00547 -0.0289 0.7194 0.0068 -6.500 -0.5642 0.01141 0.00500 -0.0287 0.7179 0.0096 -6.250 -0.5378 0.01115 0.00476 -0.0287 0.7163 0.0123 -6.000 -0.5111 0.01092 0.00452 -0.0288 0.7148 0.0142 -5.750 -0.4843 0.01068 0.00424 -0.0288 0.7133 0.0156 -5.500 -0.4573 0.01050 0.00408 -0.0289 0.7119 0.0189 -5.250 -0.4299 0.01036 0.00392 -0.0290 0.7105 0.0213 -5.000 -0.4026 0.01021 0.00374 -0.0292 0.7092 0.0231 -4.750 -0.3750 0.01011 0.00358 -0.0293 0.7079 0.0242 -4.500 -0.3471 0.01004 0.00350 -0.0296 0.7067 0.0248 -4.250 -0.3193 0.00993 0.00339 -0.0298 0.7054 0.0251 -4.000 -0.2924 0.00965 0.00307 -0.0298 0.7039 0.0257 -3.750 -0.2652 0.00940 0.00278 -0.0299 0.7025 0.0263 -3.500 -0.2379 0.00919 0.00255 -0.0300 0.7010 0.0269 -3.250 -0.2103 0.00901 0.00233 -0.0301 0.6997 0.0274 -3.000 -0.1826 0.00885 0.00215 -0.0303 0.6984 0.0281 -2.750 -0.1548 0.00870 0.00199 -0.0305 0.6972 0.0292 -2.500 -0.1270 0.00857 0.00186 -0.0306 0.6960 0.0304 -2.250 -0.0991 0.00846 0.00172 -0.0308 0.6949 0.0315 -1.750 -0.0434 0.00815 0.00151 -0.0312 0.6928 0.0570 -1.500 -0.0164 0.00781 0.00139 -0.0314 0.6917 0.1205 -1.250 0.0085 0.00711 0.00121 -0.0315 0.6906 0.2816 -1.000 0.0290 0.00567 0.00094 -0.0311 0.6894 0.6264 -0.750 0.0573 0.00565 0.00098 -0.0313 0.6882 0.6616 -0.500 0.0860 0.00566 0.00101 -0.0316 0.6871 0.6759 -0.250 0.1148 0.00566 0.00103 -0.0318 0.6859 0.6827 0.000 0.1436 0.00568 0.00104 -0.0321 0.6843 0.6888 0.250 0.1724 0.00570 0.00104 -0.0324 0.6826 0.6936 0.500 0.2010 0.00571 0.00107 -0.0327 0.6809 0.6981 0.750 0.2299 0.00573 0.00109 -0.0330 0.6766 0.7051 1.000 0.2585 0.00571 0.00109 -0.0332 0.6707 0.7079 1.250 0.2870 0.00572 0.00109 -0.0335 0.6660 0.7105 1.500 0.3158 0.00570 0.00110 -0.0338 0.6583 0.7120 1.750 0.3443 0.00571 0.00110 -0.0340 0.6469 0.7135 2.000 0.3726 0.00574 0.00109 -0.0342 0.6297 0.7149 2.250 0.4002 0.00585 0.00110 -0.0343 0.5965 0.7160 2.500 0.4173 0.00725 0.00163 -0.0331 0.3730 0.7172 2.750 0.4422 0.00772 0.00186 -0.0330 0.3044 0.7184 3.000 0.4655 0.00835 0.00214 -0.0327 0.2171 0.7195 3.250 0.4896 0.00884 0.00239 -0.0324 0.1532 0.7205 3.500 0.5142 0.00923 0.00262 -0.0322 0.1084 0.7217 3.750 0.5389 0.00962 0.00286 -0.0320 0.0711 0.7228 4.000 0.5633 0.01001 0.00313 -0.0317 0.0388 0.7240 4.250 0.5892 0.01024 0.00335 -0.0316 0.0337 0.7252 4.500 0.6152 0.01046 0.00358 -0.0315 0.0303 0.7265 4.750 0.6410 0.01068 0.00380 -0.0314 0.0273 0.7279 5.000 0.6665 0.01093 0.00405 -0.0312 0.0250 0.7293 5.250 0.6920 0.01117 0.00431 -0.0311 0.0235 0.7307 5.500 0.7181 0.01135 0.00454 -0.0310 0.0228 0.7321 5.750 0.7437 0.01155 0.00476 -0.0309 0.0197 0.7335 6.000 0.7680 0.01185 0.00503 -0.0306 0.0130 0.7351 6.250 0.7919 0.01218 0.00534 -0.0302 0.0095 0.7368 6.500 0.8151 0.01257 0.00578 -0.0296 0.0068 0.7387 6.750 0.8387 0.01290 0.00616 -0.0291 0.0064 0.7406 7.000 0.8619 0.01326 0.00656 -0.0286 0.0059 0.7425 7.250 0.8846 0.01364 0.00698 -0.0280 0.0053 0.7445 7.500 0.9067 0.01406 0.00743 -0.0274 0.0048 0.7465 8.000 0.9479 0.01511 0.00859 -0.0256 0.0039 0.7506 8.250 0.9650 0.01592 0.00957 -0.0241 0.0036 0.7531 8.500 0.9854 0.01641 0.01013 -0.0232 0.0035 0.7557 8.750 1.0045 0.01700 0.01080 -0.0221 0.0034 0.7584 9.000 1.0226 0.01766 0.01154 -0.0209 0.0033 0.7611 9.250 1.0401 0.01816 0.01211 -0.0195 0.0031 0.7639 9.500 1.0551 0.01885 0.01291 -0.0177 0.0031 0.7672 9.750 1.0702 0.01958 0.01373 -0.0161 0.0029 0.7709 10.000 1.0851 0.02035 0.01460 -0.0145 0.0028 0.7748 10.250 1.0998 0.02118 0.01554 -0.0130 0.0027 0.7788 10.500 1.1152 0.02190 0.01634 -0.0116 0.0025 0.7836 10.750 1.1288 0.02288 0.01745 -0.0101 0.0025 0.7885 11.000 1.1415 0.02396 0.01869 -0.0086 0.0024 0.7934 11.250 1.1546 0.02492 0.01977 -0.0072 0.0024 0.7993 11.500 1.1688 0.02568 0.02060 -0.0061 0.0023 0.8053 11.750 1.1806 0.02670 0.02173 -0.0047 0.0022 0.8126 12.000 1.1912 0.02785 0.02300 -0.0033 0.0021 0.8204 12.250 1.1966 0.02954 0.02488 -0.0015 0.0020 0.8301 12.500 1.1987 0.03150 0.02706 0.0005 0.0020 0.8417 12.750 1.1948 0.03405 0.02989 0.0028 0.0019 0.8570 13.000 1.1902 0.03648 0.03262 0.0050 0.0019 0.8841 13.250 1.1960 0.03933 0.03588 0.0042 0.0018 1.0000 13.500 1.1956 0.04170 0.03840 0.0053 0.0018 1.0000 13.750 1.1920 0.04444 0.04130 0.0063 0.0018 1.0000 14.000 1.1895 0.04711 0.04411 0.0070 0.0018 1.0000 14.250 1.1676 0.05220 0.04945 0.0076 0.0018 1.0000 14.500 1.1512 0.05691 0.05434 0.0074 0.0018 1.0000 14.750 1.1473 0.06025 0.05779 0.0069 0.0018 1.0000 15.000 1.1187 0.06759 0.06536 0.0047 0.0018 1.0000 15.250 1.0951 0.07522 0.07316 0.0012 0.0018 1.0000 15.500 1.0541 0.08900 0.08718 -0.0074 0.0018 1.0000