XFOIL Version 6.96 Calculated polar for: P-51D ROOT (BL17.5) 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2142 0.07513 0.07134 -0.0543 1.0000 0.0166 -19.500 -1.2208 0.07091 0.06702 -0.0562 1.0000 0.0167 -19.250 -1.2251 0.06709 0.06311 -0.0578 1.0000 0.0168 -19.000 -1.2275 0.06361 0.05955 -0.0592 1.0000 0.0171 -18.750 -1.2317 0.06001 0.05586 -0.0605 1.0000 0.0172 -18.500 -1.2336 0.05678 0.05257 -0.0616 1.0000 0.0174 -18.250 -1.2335 0.05388 0.04959 -0.0626 1.0000 0.0177 -18.000 -1.2316 0.05124 0.04690 -0.0633 1.0000 0.0180 -17.750 -1.2287 0.04882 0.04441 -0.0639 1.0000 0.0182 -17.500 -1.2243 0.04659 0.04213 -0.0644 1.0000 0.0185 -17.000 -1.2073 0.04233 0.03774 -0.0664 0.9689 0.0190 -16.750 -1.1878 0.04043 0.03577 -0.0690 0.9634 0.0194 -16.500 -1.1667 0.03853 0.03378 -0.0720 0.9572 0.0198 -16.250 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0.0184 0.00709 0.00155 -0.0366 0.5240 0.5461 -1.000 0.0471 0.00709 0.00157 -0.0368 0.5209 0.5561 -0.750 0.0761 0.00711 0.00158 -0.0370 0.5180 0.5621 -0.500 0.1050 0.00714 0.00158 -0.0372 0.5153 0.5661 -0.250 0.1335 0.00717 0.00161 -0.0373 0.5115 0.5719 0.000 0.1624 0.00720 0.00163 -0.0375 0.5078 0.5769 0.250 0.1915 0.00723 0.00165 -0.0377 0.5052 0.5820 0.500 0.2202 0.00724 0.00168 -0.0379 0.5023 0.5869 0.750 0.2488 0.00727 0.00171 -0.0380 0.4983 0.5900 1.000 0.2773 0.00733 0.00174 -0.0381 0.4941 0.5926 1.250 0.3062 0.00736 0.00177 -0.0383 0.4914 0.5949 1.500 0.3352 0.00739 0.00179 -0.0386 0.4884 0.5971 1.750 0.3641 0.00743 0.00182 -0.0388 0.4853 0.5986 2.000 0.3926 0.00745 0.00186 -0.0389 0.4816 0.6005 2.250 0.4207 0.00750 0.00190 -0.0390 0.4768 0.6022 2.500 0.4494 0.00753 0.00194 -0.0392 0.4719 0.6039 2.750 0.4779 0.00756 0.00199 -0.0393 0.4676 0.6056 3.000 0.5062 0.00761 0.00204 -0.0394 0.4633 0.6076 3.250 0.5343 0.00768 0.00210 -0.0395 0.4588 0.6095 3.500 0.5628 0.00773 0.00216 -0.0396 0.4518 0.6114 3.750 0.5904 0.00782 0.00223 -0.0396 0.4427 0.6131 4.000 0.6181 0.00791 0.00230 -0.0396 0.4302 0.6146 4.250 0.6441 0.00810 0.00239 -0.0394 0.4027 0.6160 4.500 0.6567 0.00919 0.00290 -0.0371 0.2794 0.6178 4.750 0.6796 0.00958 0.00316 -0.0364 0.2512 0.6197 5.000 0.7032 0.00991 0.00339 -0.0358 0.2241 0.6216 5.250 0.7224 0.01049 0.00371 -0.0346 0.1729 0.6236 5.500 0.7452 0.01081 0.00395 -0.0338 0.1537 0.6258 5.750 0.7693 0.01105 0.00416 -0.0333 0.1451 0.6281 6.000 0.7938 0.01125 0.00435 -0.0328 0.1386 0.6302 6.250 0.8174 0.01149 0.00457 -0.0322 0.1315 0.6321 6.750 0.8644 0.01191 0.00499 -0.0309 0.1197 0.6360 7.000 0.8861 0.01217 0.00523 -0.0300 0.1124 0.6383 7.250 0.9083 0.01239 0.00546 -0.0291 0.1058 0.6407 7.500 0.9282 0.01270 0.00573 -0.0279 0.0962 0.6432 7.750 0.9450 0.01306 0.00602 -0.0261 0.0839 0.6457 8.000 0.9582 0.01343 0.00635 -0.0237 0.0724 0.6482 8.250 0.9718 0.01385 0.00672 -0.0214 0.0642 0.6507 8.500 0.9857 0.01426 0.00713 -0.0192 0.0581 0.6538 8.750 1.0012 0.01465 0.00753 -0.0174 0.0540 0.6570 9.000 1.0156 0.01510 0.00799 -0.0154 0.0499 0.6602 9.250 1.0316 0.01551 0.00841 -0.0138 0.0472 0.6634 9.500 1.0465 0.01598 0.00889 -0.0120 0.0442 0.6665 9.750 1.0612 0.01647 0.00939 -0.0103 0.0417 0.6698 10.000 1.0761 0.01695 0.00990 -0.0087 0.0394 0.6738 10.250 1.0905 0.01748 0.01045 -0.0070 0.0375 0.6780 10.500 1.1044 0.01804 0.01104 -0.0054 0.0358 0.6826 10.750 1.1193 0.01857 0.01162 -0.0039 0.0347 0.6876 11.000 1.1330 0.01916 0.01225 -0.0023 0.0335 0.6941 11.250 1.1460 0.01982 0.01294 -0.0007 0.0322 0.7008 11.500 1.1581 0.02052 0.01369 0.0009 0.0311 0.7089 11.750 1.1711 0.02121 0.01444 0.0024 0.0302 0.7188 12.000 1.1837 0.02190 0.01523 0.0038 0.0296 0.7337 12.250 1.1949 0.02264 0.01610 0.0054 0.0288 0.7594 12.500 1.2018 0.02326 0.01702 0.0078 0.0282 0.8526 12.750 1.2310 0.02411 0.01815 0.0054 0.0272 0.9489 13.000 1.2511 0.02530 0.01938 0.0045 0.0263 1.0000 13.250 1.2630 0.02634 0.02046 0.0054 0.0258 1.0000 13.500 1.2749 0.02742 0.02158 0.0062 0.0252 1.0000 13.750 1.2858 0.02862 0.02283 0.0070 0.0248 1.0000 14.000 1.2966 0.02988 0.02412 0.0077 0.0243 1.0000 14.250 1.3066 0.03123 0.02551 0.0083 0.0237 1.0000 14.500 1.3159 0.03270 0.02701 0.0088 0.0232 1.0000 14.750 1.3244 0.03428 0.02863 0.0093 0.0226 1.0000 15.000 1.3316 0.03604 0.03043 0.0097 0.0221 1.0000 15.250 1.3406 0.03765 0.03209 0.0101 0.0218 1.0000 15.500 1.3502 0.03923 0.03373 0.0103 0.0215 1.0000 15.750 1.3584 0.04097 0.03552 0.0105 0.0211 1.0000 16.000 1.3663 0.04276 0.03737 0.0106 0.0207 1.0000 16.250 1.3737 0.04462 0.03928 0.0107 0.0202 1.0000 16.500 1.3805 0.04655 0.04125 0.0108 0.0198 1.0000 16.750 1.3859 0.04865 0.04341 0.0108 0.0195 1.0000 17.000 1.3909 0.05082 0.04563 0.0107 0.0191 1.0000 17.250 1.3950 0.05312 0.04797 0.0106 0.0187 1.0000 17.500 1.3971 0.05565 0.05056 0.0104 0.0183 1.0000 17.750 1.4014 0.05797 0.05295 0.0102 0.0181 1.0000 18.000 1.4056 0.06036 0.05540 0.0099 0.0178 1.0000 18.250 1.4081 0.06299 0.05811 0.0095 0.0177 1.0000 18.500 1.4124 0.06540 0.06058 0.0091 0.0171 1.0000 18.750 1.4134 0.06828 0.06353 0.0085 0.0169 1.0000 19.000 1.4147 0.07113 0.06645 0.0079 0.0166 1.0000 19.250 1.4145 0.07427 0.06965 0.0071 0.0163 1.0000