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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0156 0.10536 0.10163 -0.0400 1.0000 0.0207 -19.500 -1.0290 0.09907 0.09525 -0.0436 1.0000 0.0209 -19.250 -1.0409 0.09320 0.08927 -0.0469 1.0000 0.0211 -19.000 -1.0511 0.08774 0.08371 -0.0500 1.0000 0.0212 -18.750 -1.0592 0.08276 0.07863 -0.0527 1.0000 0.0214 -18.500 -1.0661 0.07808 0.07385 -0.0551 1.0000 0.0216 -18.250 -1.0713 0.07378 0.06944 -0.0572 1.0000 0.0218 -18.000 -1.0747 0.06987 0.06543 -0.0591 1.0000 0.0221 -17.750 -1.0771 0.06623 0.06169 -0.0608 1.0000 0.0223 -17.500 -1.0773 0.06294 0.05831 -0.0622 1.0000 0.0227 -17.250 -1.0779 0.05976 0.05503 -0.0634 1.0000 0.0229 -17.000 -1.0761 0.05693 0.05210 -0.0644 1.0000 0.0233 -16.750 -1.0757 0.05408 0.04915 -0.0652 1.0000 0.0234 -16.500 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0.00295 -0.0378 0.5011 0.6311 3.000 0.4982 0.00956 0.00300 -0.0378 0.4960 0.6330 3.250 0.5259 0.00961 0.00306 -0.0378 0.4915 0.6348 3.500 0.5541 0.00963 0.00314 -0.0379 0.4873 0.6366 3.750 0.5818 0.00967 0.00321 -0.0379 0.4818 0.6385 4.000 0.6088 0.00975 0.00329 -0.0378 0.4758 0.6405 4.250 0.6367 0.00979 0.00338 -0.0379 0.4699 0.6426 4.500 0.6638 0.00986 0.00347 -0.0378 0.4624 0.6448 4.750 0.6908 0.00994 0.00356 -0.0376 0.4520 0.6473 5.000 0.7166 0.01005 0.00365 -0.0373 0.4341 0.6497 5.250 0.7388 0.01030 0.00376 -0.0364 0.3914 0.6518 5.500 0.7452 0.01151 0.00436 -0.0332 0.2754 0.6540 5.750 0.7640 0.01204 0.00475 -0.0319 0.2436 0.6563 6.000 0.7835 0.01249 0.00509 -0.0306 0.2141 0.6587 6.250 0.8017 0.01299 0.00545 -0.0292 0.1807 0.6613 6.500 0.8207 0.01341 0.00577 -0.0279 0.1620 0.6640 6.750 0.8407 0.01375 0.00608 -0.0268 0.1517 0.6666 7.000 0.8595 0.01410 0.00641 -0.0254 0.1427 0.6694 7.250 0.8782 0.01435 0.00670 -0.0239 0.1362 0.6725 7.500 0.8938 0.01467 0.00702 -0.0219 0.1290 0.6760 7.750 0.9104 0.01499 0.00736 -0.0202 0.1228 0.6796 8.000 0.9263 0.01537 0.00774 -0.0184 0.1154 0.6831 8.250 0.9422 0.01576 0.00815 -0.0166 0.1082 0.6865 8.500 0.9564 0.01623 0.00861 -0.0147 0.0991 0.6905 8.750 0.9701 0.01674 0.00910 -0.0128 0.0881 0.6951 9.000 0.9821 0.01735 0.00967 -0.0107 0.0768 0.6999 9.250 0.9946 0.01795 0.01027 -0.0088 0.0687 0.7053 9.500 1.0069 0.01856 0.01091 -0.0068 0.0625 0.7120 10.000 1.0312 0.01985 0.01229 -0.0032 0.0540 0.7298 10.250 1.0427 0.02054 0.01304 -0.0013 0.0510 0.7423 10.500 1.0535 0.02124 0.01385 0.0006 0.0484 0.7615 10.750 1.0638 0.02186 0.01465 0.0026 0.0461 0.7984 11.000 1.0717 0.02252 0.01552 0.0050 0.0443 0.8641 11.250 1.1015 0.02348 0.01668 0.0025 0.0415 0.9382 11.500 1.1193 0.02440 0.01765 0.0025 0.0400 1.0000 11.750 1.1304 0.02543 0.01871 0.0036 0.0386 1.0000 12.000 1.1406 0.02657 0.01988 0.0048 0.0374 1.0000 12.250 1.1491 0.02788 0.02120 0.0059 0.0362 1.0000 12.500 1.1598 0.02907 0.02245 0.0068 0.0354 1.0000 12.750 1.1706 0.03030 0.02374 0.0076 0.0344 1.0000 13.000 1.1804 0.03165 0.02513 0.0083 0.0335 1.0000 13.250 1.1893 0.03312 0.02665 0.0090 0.0327 1.0000 13.500 1.1973 0.03471 0.02827 0.0095 0.0320 1.0000 13.750 1.2040 0.03648 0.03007 0.0101 0.0312 1.0000 14.000 1.2109 0.03828 0.03192 0.0105 0.0306 1.0000 14.250 1.2201 0.03988 0.03360 0.0108 0.0300 1.0000 14.500 1.2284 0.04162 0.03540 0.0110 0.0293 1.0000 14.750 1.2358 0.04347 0.03732 0.0112 0.0288 1.0000 15.000 1.2429 0.04536 0.03927 0.0114 0.0282 1.0000 15.250 1.2491 0.04739 0.04134 0.0114 0.0276 1.0000 15.500 1.2541 0.04956 0.04357 0.0114 0.0271 1.0000 15.750 1.2572 0.05198 0.04603 0.0114 0.0265 1.0000 16.000 1.2596 0.05449 0.04860 0.0112 0.0261 1.0000 16.250 1.2659 0.05664 0.05083 0.0110 0.0256 1.0000 16.500 1.2711 0.05893 0.05321 0.0108 0.0251 1.0000 16.750 1.2752 0.06139 0.05574 0.0105 0.0247 1.0000 17.000 1.2787 0.06397 0.05840 0.0100 0.0242 1.0000 17.250 1.2822 0.06658 0.06109 0.0095 0.0238 1.0000 17.500 1.2841 0.06946 0.06404 0.0089 0.0234 1.0000 17.750 1.2848 0.07253 0.06718 0.0081 0.0230 1.0000 18.000 1.2847 0.07579 0.07051 0.0072 0.0226 1.0000 18.250 1.2822 0.07941 0.07420 0.0061 0.0223 1.0000 18.500 1.2787 0.08324 0.07810 0.0049 0.0220 1.0000 18.750 1.2797 0.08653 0.08150 0.0038 0.0217 1.0000 19.000 1.2779 0.09030 0.08537 0.0024 0.0214 1.0000 19.250 1.2768 0.09404 0.08921 0.0009 0.0210 1.0000