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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -1.1370 0.08211 0.07858 -0.0519 1.0000 0.0198 -19.250 -1.1486 0.07705 0.07342 -0.0543 1.0000 0.0201 -19.000 -1.1622 0.07191 0.06819 -0.0565 1.0000 0.0205 -18.750 -1.1664 0.06807 0.06429 -0.0582 1.0000 0.0207 -18.500 -1.1695 0.06442 0.06058 -0.0597 1.0000 0.0209 -18.250 -1.1705 0.06115 0.05723 -0.0610 1.0000 0.0211 -18.000 -1.1691 0.05826 0.05428 -0.0621 1.0000 0.0214 -17.750 -1.1674 0.05547 0.05143 -0.0631 1.0000 0.0217 -17.500 -1.1640 0.05294 0.04883 -0.0639 1.0000 0.0219 -17.250 -1.1612 0.05041 0.04623 -0.0645 1.0000 0.0223 -17.000 -1.1573 0.04809 0.04384 -0.0651 1.0000 0.0225 -16.750 -1.1519 0.04597 0.04165 -0.0655 1.0000 0.0227 -16.500 -1.1444 0.04409 0.03970 -0.0659 1.0000 0.0231 -16.250 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0.00231 -0.0392 0.5114 0.6338 2.750 0.4785 0.00766 0.00236 -0.0393 0.5078 0.6358 3.000 0.5067 0.00772 0.00241 -0.0394 0.5035 0.6378 3.250 0.5356 0.00772 0.00245 -0.0396 0.4995 0.6399 3.500 0.5642 0.00775 0.00250 -0.0398 0.4960 0.6418 3.750 0.5925 0.00781 0.00255 -0.0399 0.4917 0.6436 4.000 0.6203 0.00790 0.00262 -0.0399 0.4872 0.6452 4.250 0.6490 0.00788 0.00266 -0.0401 0.4819 0.6472 4.500 0.6763 0.00792 0.00269 -0.0400 0.4723 0.6497 4.750 0.7042 0.00794 0.00275 -0.0401 0.4623 0.6520 5.000 0.7311 0.00803 0.00281 -0.0399 0.4468 0.6544 5.250 0.7569 0.00818 0.00289 -0.0396 0.4231 0.6568 5.500 0.7750 0.00882 0.00316 -0.0382 0.3407 0.6592 5.750 0.7900 0.00970 0.00367 -0.0363 0.2678 0.6613 6.000 0.8122 0.01011 0.00395 -0.0354 0.2434 0.6632 6.250 0.8342 0.01044 0.00421 -0.0346 0.2169 0.6662 6.500 0.8539 0.01089 0.00451 -0.0334 0.1830 0.6690 6.750 0.8743 0.01127 0.00480 -0.0323 0.1630 0.6718 7.000 0.8955 0.01159 0.00508 -0.0313 0.1514 0.6747 7.250 0.9178 0.01185 0.00533 -0.0304 0.1436 0.6776 7.500 0.9380 0.01218 0.00562 -0.0292 0.1348 0.6804 7.750 0.9597 0.01238 0.00585 -0.0283 0.1288 0.6844 8.000 0.9778 0.01269 0.00615 -0.0267 0.1204 0.6883 8.250 0.9959 0.01290 0.00638 -0.0251 0.1135 0.6923 8.500 1.0107 0.01323 0.00668 -0.0230 0.1044 0.6962 8.750 1.0237 0.01366 0.00706 -0.0206 0.0919 0.7008 9.000 1.0347 0.01416 0.00753 -0.0180 0.0786 0.7063 9.250 1.0455 0.01472 0.00805 -0.0155 0.0681 0.7123 9.500 1.0569 0.01528 0.00860 -0.0132 0.0607 0.7193 9.750 1.0677 0.01587 0.00920 -0.0109 0.0551 0.7289 10.000 1.0815 0.01634 0.00974 -0.0090 0.0517 0.7422 10.250 1.0914 0.01694 0.01041 -0.0066 0.0479 0.7656 10.500 1.1015 0.01733 0.01104 -0.0041 0.0459 0.8276 10.750 1.1103 0.01768 0.01165 -0.0012 0.0438 0.9098 11.000 1.1473 0.01863 0.01268 -0.0050 0.0403 1.0000 11.250 1.1626 0.01924 0.01333 -0.0038 0.0393 1.0000 11.500 1.1762 0.01996 0.01407 -0.0024 0.0379 1.0000 11.750 1.1884 0.02079 0.01491 -0.0010 0.0366 1.0000 12.000 1.1971 0.02186 0.01599 0.0007 0.0351 1.0000 12.250 1.2086 0.02280 0.01697 0.0020 0.0343 1.0000 12.500 1.2221 0.02365 0.01786 0.0031 0.0336 1.0000 12.750 1.2340 0.02463 0.01888 0.0042 0.0328 1.0000 13.000 1.2452 0.02570 0.01997 0.0052 0.0318 1.0000 13.250 1.2540 0.02698 0.02128 0.0063 0.0310 1.0000 13.500 1.2590 0.02863 0.02296 0.0074 0.0299 1.0000 13.750 1.2675 0.03008 0.02446 0.0082 0.0295 1.0000 14.000 1.2776 0.03143 0.02587 0.0089 0.0291 1.0000 14.250 1.2885 0.03277 0.02726 0.0093 0.0285 1.0000 14.500 1.2992 0.03417 0.02871 0.0097 0.0278 1.0000 14.750 1.3081 0.03576 0.03035 0.0101 0.0273 1.0000 15.000 1.3156 0.03752 0.03214 0.0105 0.0267 1.0000 15.250 1.3209 0.03951 0.03417 0.0108 0.0261 1.0000 15.500 1.3211 0.04205 0.03676 0.0111 0.0254 1.0000 15.750 1.3267 0.04411 0.03888 0.0112 0.0251 1.0000 16.000 1.3358 0.04582 0.04066 0.0113 0.0247 1.0000 16.250 1.3432 0.04771 0.04261 0.0113 0.0243 1.0000 16.500 1.3490 0.04982 0.04478 0.0113 0.0238 1.0000 16.750 1.3553 0.05189 0.04690 0.0112 0.0234 1.0000 17.000 1.3602 0.05413 0.04919 0.0110 0.0229 1.0000 17.250 1.3629 0.05663 0.05174 0.0108 0.0226 1.0000 17.500 1.3635 0.05940 0.05457 0.0105 0.0222 1.0000 17.750 1.3611 0.06259 0.05782 0.0101 0.0218 1.0000 18.000 1.3542 0.06636 0.06167 0.0095 0.0213 1.0000 18.250 1.3586 0.06887 0.06425 0.0089 0.0211 1.0000 18.500 1.3634 0.07137 0.06682 0.0084 0.0208 1.0000 18.750 1.3639 0.07448 0.07002 0.0076 0.0205 1.0000 19.000 1.3646 0.07757 0.07318 0.0068 0.0202 1.0000 19.250 1.3660 0.08063 0.07631 0.0058 0.0198 1.0000