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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.8276 0.09130 0.08664 -0.0532 1.0000 0.0320 -16.500 -0.8636 0.08140 0.07645 -0.0593 1.0000 0.0321 -16.250 -0.8884 0.07421 0.06901 -0.0633 1.0000 0.0323 -16.000 -0.9076 0.06840 0.06297 -0.0661 1.0000 0.0325 -15.750 -0.9230 0.06351 0.05785 -0.0681 1.0000 0.0328 -15.500 -0.9354 0.05930 0.05340 -0.0695 1.0000 0.0331 -15.250 -0.9458 0.05559 0.04945 -0.0705 1.0000 0.0335 -15.000 -0.9427 0.05329 0.04709 -0.0708 1.0000 0.0338 -14.750 -0.9381 0.05132 0.04509 -0.0711 1.0000 0.0343 -14.500 -0.9344 0.04926 0.04297 -0.0712 1.0000 0.0347 -14.250 -0.9306 0.04727 0.04088 -0.0713 1.0000 0.0351 -14.000 -0.9266 0.04534 0.03886 -0.0712 1.0000 0.0357 -13.750 -0.9219 0.04346 0.03687 -0.0710 1.0000 0.0362 -13.500 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0.5836 0.6629 1.250 0.2950 0.01328 0.00508 -0.0356 0.5804 0.6656 1.750 0.3508 0.01335 0.00518 -0.0358 0.5725 0.6699 2.000 0.3786 0.01338 0.00525 -0.0359 0.5685 0.6721 2.250 0.4064 0.01345 0.00530 -0.0359 0.5643 0.6746 2.500 0.4340 0.01351 0.00537 -0.0359 0.5595 0.6774 2.750 0.4611 0.01354 0.00545 -0.0359 0.5536 0.6801 3.000 0.4887 0.01359 0.00550 -0.0359 0.5487 0.6827 3.250 0.5167 0.01369 0.00557 -0.0360 0.5450 0.6853 3.500 0.5436 0.01372 0.00570 -0.0359 0.5402 0.6874 3.750 0.5706 0.01376 0.00582 -0.0358 0.5351 0.6900 4.000 0.5977 0.01382 0.00593 -0.0357 0.5304 0.6931 4.250 0.6244 0.01389 0.00602 -0.0355 0.5246 0.6964 4.500 0.6505 0.01393 0.00614 -0.0352 0.5171 0.6997 4.750 0.6771 0.01399 0.00622 -0.0351 0.5109 0.7027 5.000 0.7030 0.01404 0.00640 -0.0348 0.5047 0.7054 5.250 0.7287 0.01408 0.00654 -0.0344 0.4973 0.7086 5.500 0.7541 0.01414 0.00667 -0.0340 0.4892 0.7121 5.750 0.7784 0.01419 0.00677 -0.0334 0.4775 0.7162 6.000 0.8012 0.01423 0.00687 -0.0325 0.4606 0.7204 6.250 0.8221 0.01428 0.00699 -0.0312 0.4331 0.7246 6.500 0.8366 0.01452 0.00704 -0.0290 0.3702 0.7294 6.750 0.8373 0.01546 0.00748 -0.0247 0.2917 0.7347 7.000 0.8456 0.01621 0.00808 -0.0218 0.2591 0.7398 7.250 0.8558 0.01683 0.00865 -0.0192 0.2355 0.7460 7.500 0.8662 0.01735 0.00914 -0.0165 0.2124 0.7533 7.750 0.8748 0.01793 0.00970 -0.0136 0.1910 0.7617 8.250 0.8936 0.01921 0.01098 -0.0085 0.1621 0.7869 8.500 0.9043 0.01985 0.01169 -0.0063 0.1521 0.8060 8.750 0.9147 0.02052 0.01243 -0.0041 0.1434 0.8336 9.000 0.9280 0.02111 0.01314 -0.0023 0.1349 0.8698 9.250 0.9471 0.02189 0.01401 -0.0021 0.1254 0.9208 9.500 0.9679 0.02263 0.01481 -0.0024 0.1147 1.0000 9.750 0.9805 0.02346 0.01563 -0.0011 0.1053 1.0000 10.000 0.9914 0.02441 0.01654 0.0003 0.0956 1.0000 10.250 1.0014 0.02545 0.01754 0.0018 0.0871 1.0000 10.500 1.0111 0.02656 0.01862 0.0031 0.0794 1.0000 10.750 1.0199 0.02776 0.01982 0.0044 0.0738 1.0000 11.000 1.0282 0.02905 0.02110 0.0057 0.0688 1.0000 11.250 1.0359 0.03043 0.02249 0.0068 0.0647 1.0000 11.500 1.0447 0.03179 0.02389 0.0078 0.0615 1.0000 11.750 1.0515 0.03336 0.02546 0.0088 0.0587 1.0000 12.000 1.0583 0.03498 0.02711 0.0096 0.0565 1.0000 12.250 1.0669 0.03651 0.02871 0.0103 0.0544 1.0000 12.500 1.0747 0.03814 0.03040 0.0109 0.0525 1.0000 12.750 1.0812 0.03992 0.03221 0.0115 0.0509 1.0000 13.000 1.0857 0.04192 0.03422 0.0120 0.0494 1.0000 13.250 1.0942 0.04362 0.03600 0.0123 0.0480 1.0000 13.500 1.1021 0.04540 0.03787 0.0127 0.0466 1.0000 13.750 1.1094 0.04726 0.03979 0.0129 0.0452 1.0000 14.000 1.1162 0.04921 0.04180 0.0131 0.0442 1.0000 14.250 1.1217 0.05131 0.04393 0.0132 0.0432 1.0000 14.500 1.1259 0.05355 0.04618 0.0133 0.0422 1.0000 14.750 1.1335 0.05552 0.04825 0.0134 0.0414 1.0000 15.000 1.1405 0.05759 0.05043 0.0134 0.0404 1.0000 15.250 1.1467 0.05976 0.05270 0.0133 0.0395 1.0000 15.500 1.1521 0.06205 0.05506 0.0131 0.0385 1.0000 15.750 1.1570 0.06444 0.05752 0.0128 0.0377 1.0000 16.000 1.1614 0.06691 0.06005 0.0124 0.0371 1.0000 16.250 1.1653 0.06946 0.06262 0.0120 0.0364 1.0000 16.500 1.1694 0.07205 0.06530 0.0116 0.0357 1.0000 16.750 1.1725 0.07486 0.06826 0.0110 0.0351 1.0000 17.000 1.1747 0.07784 0.07138 0.0102 0.0344 1.0000 17.250 1.1758 0.08102 0.07468 0.0093 0.0336 1.0000 17.500 1.1768 0.08426 0.07802 0.0083 0.0330 1.0000 17.750 1.1773 0.08761 0.08147 0.0071 0.0324 1.0000 18.000 1.1773 0.09107 0.08501 0.0058 0.0319 1.0000 18.250 1.1776 0.09452 0.08853 0.0045 0.0314 1.0000 18.500 1.1785 0.09787 0.09192 0.0032 0.0309 1.0000 18.750 1.1739 0.10233 0.09654 0.0012 0.0304 1.0000 19.000 1.1667 0.10733 0.10174 -0.0012 0.0300 1.0000 19.250 1.1584 0.11267 0.10727 -0.0039 0.0295 1.0000