XFOIL Version 6.96 Calculated polar for: AH 94-W-301 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.1646 0.09521 0.09050 -0.0314 1.0000 0.1762 -19.000 -1.1726 0.09126 0.08646 -0.0325 1.0000 0.1797 -18.750 -1.1672 0.08907 0.08428 -0.0332 1.0000 0.1830 -18.500 -1.1623 0.08684 0.08209 -0.0339 1.0000 0.1865 -18.250 -1.1652 0.08362 0.07885 -0.0347 1.0000 0.1902 -18.000 -1.1705 0.08015 0.07528 -0.0355 1.0000 0.1937 -17.750 -1.1634 0.07824 0.07342 -0.0360 1.0000 0.1974 -17.500 -1.1624 0.07561 0.07082 -0.0366 1.0000 0.2012 -17.250 -1.1629 0.07278 0.06795 -0.0372 1.0000 0.2050 -17.000 -1.1702 0.06920 0.06426 -0.0379 1.0000 0.2084 -16.750 -1.1600 0.06775 0.06289 -0.0382 1.0000 0.2122 -16.500 -1.1564 0.06550 0.06067 -0.0386 1.0000 0.2160 -16.250 -1.1595 0.06251 0.05762 -0.0390 1.0000 0.2200 -16.000 -1.1602 0.05981 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0.4756 3.000 0.6207 0.01453 0.00740 -0.0959 0.4653 0.4787 3.250 0.6517 0.01460 0.00747 -0.0965 0.4625 0.4817 3.500 0.6828 0.01468 0.00754 -0.0972 0.4598 0.4840 3.750 0.7133 0.01465 0.00756 -0.0977 0.4573 0.4877 4.000 0.7438 0.01472 0.00765 -0.0983 0.4548 0.4907 4.250 0.7745 0.01489 0.00781 -0.0988 0.4519 0.4937 4.500 0.8052 0.01508 0.00801 -0.0994 0.4491 0.4969 4.750 0.8351 0.01515 0.00813 -0.0998 0.4469 0.5002 5.000 0.8652 0.01524 0.00825 -0.1002 0.4445 0.5030 5.250 0.8953 0.01534 0.00835 -0.1007 0.4420 0.5054 5.500 0.9249 0.01534 0.00842 -0.1010 0.4394 0.5091 5.750 0.9544 0.01542 0.00854 -0.1013 0.4368 0.5123 6.000 0.9840 0.01557 0.00869 -0.1016 0.4342 0.5155 6.250 1.0144 0.01584 0.00893 -0.1022 0.4312 0.5189 6.500 1.0433 0.01600 0.00913 -0.1024 0.4291 0.5222 6.750 1.0716 0.01611 0.00929 -0.1025 0.4267 0.5249 7.000 1.0999 0.01619 0.00942 -0.1026 0.4241 0.5279 7.250 1.1280 0.01626 0.00956 -0.1026 0.4215 0.5315 7.500 1.1559 0.01638 0.00972 -0.1026 0.4189 0.5349 7.750 1.1837 0.01653 0.00989 -0.1026 0.4162 0.5384 8.000 1.2124 0.01677 0.01011 -0.1028 0.4131 0.5419 8.250 1.2399 0.01702 0.01038 -0.1027 0.4103 0.5451 8.500 1.2649 0.01715 0.01057 -0.1022 0.4077 0.5477 8.750 1.2898 0.01721 0.01072 -0.1017 0.4044 0.5515 9.000 1.3143 0.01732 0.01089 -0.1010 0.4010 0.5551 9.250 1.3385 0.01748 0.01108 -0.1004 0.3978 0.5588 9.500 1.3640 0.01775 0.01132 -0.1000 0.3941 0.5625 9.750 1.3847 0.01796 0.01159 -0.0987 0.3906 0.5660 10.000 1.4023 0.01813 0.01183 -0.0969 0.3865 0.5690 10.250 1.4171 0.01829 0.01204 -0.0946 0.3823 0.5721 10.500 1.4315 0.01852 0.01230 -0.0922 0.3786 0.5760 10.750 1.4508 0.01891 0.01268 -0.0908 0.3744 0.5798 11.000 1.4655 0.01930 0.01319 -0.0888 0.3710 0.5836 11.250 1.4814 0.01972 0.01370 -0.0870 0.3667 0.5875 11.500 1.4967 0.02023 0.01421 -0.0853 0.3622 0.5910 11.750 1.5109 0.02086 0.01480 -0.0835 0.3575 0.5941 12.000 1.5251 0.02146 0.01554 -0.0820 0.3532 0.5986 12.250 1.5386 0.02219 0.01637 -0.0805 0.3481 0.6025 12.500 1.5496 0.02312 0.01732 -0.0789 0.3430 0.6063 12.750 1.5595 0.02421 0.01843 -0.0773 0.3379 0.6104 13.000 1.5715 0.02530 0.01960 -0.0762 0.3323 0.6144 13.250 1.5797 0.02667 0.02101 -0.0750 0.3262 0.6183 13.500 1.5859 0.02825 0.02264 -0.0737 0.3204 0.6229 13.750 1.5939 0.02983 0.02433 -0.0728 0.3137 0.6271 14.000 1.5942 0.03200 0.02650 -0.0715 0.3066 0.6310 14.250 1.5980 0.03404 0.02861 -0.0706 0.2996 0.6351 14.500 1.5950 0.03664 0.03122 -0.0694 0.2916 0.6386 14.750 1.5919 0.03933 0.03396 -0.0685 0.2838 0.6427 15.000 1.5829 0.04260 0.03727 -0.0674 0.2748 0.6468 15.250 1.5749 0.04589 0.04062 -0.0665 0.2660 0.6510 15.500 1.5588 0.05001 0.04474 -0.0656 0.2566 0.6547 15.750 1.5492 0.05368 0.04845 -0.0650 0.2469 0.6588 16.000 1.5324 0.05810 0.05286 -0.0643 0.2373 0.6620 16.250 1.5152 0.06268 0.05746 -0.0639 0.2270 0.6656 16.500 1.5013 0.06700 0.06183 -0.0636 0.2170 0.6695 16.750 1.4835 0.07177 0.06660 -0.0633 0.2073 0.6732 17.000 1.4680 0.07639 0.07123 -0.0632 0.1976 0.6770 17.250 1.4541 0.08093 0.07577 -0.0633 0.1883 0.6810 17.500 1.4381 0.08575 0.08057 -0.0634 0.1795 0.6846 17.750 1.4266 0.09011 0.08495 -0.0637 0.1705 0.6890