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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.0719 0.09765 0.09269 -0.0320 1.0000 0.1584 -18.250 -1.0745 0.09438 0.08941 -0.0329 1.0000 0.1619 -18.000 -1.0717 0.09175 0.08676 -0.0337 1.0000 0.1653 -17.750 -1.0680 0.08925 0.08422 -0.0344 1.0000 0.1681 -17.500 -1.0711 0.08603 0.08101 -0.0352 1.0000 0.1716 -17.250 -1.0696 0.08335 0.07833 -0.0359 1.0000 0.1751 -17.000 -1.0666 0.08083 0.07579 -0.0365 1.0000 0.1784 -16.750 -1.0648 0.07818 0.07311 -0.0371 1.0000 0.1815 -16.500 -1.0652 0.07540 0.07035 -0.0376 1.0000 0.1852 -16.250 -1.0649 0.07269 0.06763 -0.0381 1.0000 0.1891 -16.000 -1.0629 0.07017 0.06507 -0.0386 1.0000 0.1926 -15.750 -1.0589 0.06790 0.06280 -0.0389 1.0000 0.1958 -15.500 -1.0601 0.06515 0.06006 -0.0393 1.0000 0.1995 -15.250 -1.0561 0.06251 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0.00546 -0.0827 0.4727 0.4040 -0.500 0.1729 0.01314 0.00546 -0.0835 0.4698 0.4062 -0.250 0.2050 0.01309 0.00546 -0.0845 0.4676 0.4093 0.000 0.2370 0.01307 0.00548 -0.0854 0.4648 0.4126 0.250 0.2689 0.01307 0.00550 -0.0863 0.4619 0.4157 0.500 0.3005 0.01308 0.00551 -0.0871 0.4592 0.4186 0.750 0.3320 0.01311 0.00553 -0.0879 0.4565 0.4213 1.000 0.3633 0.01316 0.00554 -0.0886 0.4539 0.4237 1.250 0.3944 0.01321 0.00557 -0.0894 0.4513 0.4264 1.500 0.4257 0.01323 0.00563 -0.0901 0.4489 0.4296 1.750 0.4575 0.01324 0.00569 -0.0909 0.4466 0.4327 2.000 0.4889 0.01327 0.00575 -0.0917 0.4439 0.4357 2.250 0.5201 0.01331 0.00580 -0.0924 0.4411 0.4385 2.500 0.5511 0.01337 0.00585 -0.0930 0.4386 0.4412 2.750 0.5819 0.01345 0.00591 -0.0936 0.4361 0.4437 3.000 0.6124 0.01351 0.00598 -0.0942 0.4336 0.4467 3.250 0.6426 0.01360 0.00608 -0.0947 0.4308 0.4498 3.500 0.6736 0.01365 0.00618 -0.0953 0.4286 0.4528 3.750 0.7044 0.01371 0.00628 -0.0959 0.4262 0.4557 4.000 0.7350 0.01378 0.00637 -0.0965 0.4238 0.4587 4.250 0.7652 0.01387 0.00647 -0.0969 0.4213 0.4617 4.500 0.7951 0.01397 0.00657 -0.0973 0.4186 0.4642 4.750 0.8246 0.01406 0.00668 -0.0977 0.4158 0.4672 5.000 0.8537 0.01418 0.00682 -0.0980 0.4131 0.4701 5.250 0.8829 0.01430 0.00696 -0.0982 0.4109 0.4730 5.500 0.9128 0.01439 0.00711 -0.0986 0.4089 0.4761 5.750 0.9422 0.01450 0.00725 -0.0989 0.4064 0.4793 6.000 0.9712 0.01462 0.00739 -0.0991 0.4037 0.4823 6.250 0.9997 0.01474 0.00754 -0.0993 0.4010 0.4848 6.500 1.0278 0.01487 0.00770 -0.0993 0.3985 0.4878 6.750 1.0552 0.01503 0.00788 -0.0993 0.3960 0.4907 7.000 1.0817 0.01522 0.00808 -0.0991 0.3933 0.4937 7.250 1.1096 0.01536 0.00828 -0.0991 0.3910 0.4970 7.500 1.1371 0.01550 0.00848 -0.0990 0.3886 0.5004 7.750 1.1638 0.01567 0.00868 -0.0988 0.3859 0.5033 8.000 1.1895 0.01584 0.00888 -0.0984 0.3828 0.5059 8.250 1.2140 0.01603 0.00911 -0.0979 0.3799 0.5090 8.500 1.2369 0.01626 0.00936 -0.0970 0.3767 0.5120 8.750 1.2593 0.01650 0.00963 -0.0961 0.3736 0.5152 9.000 1.2824 0.01669 0.00989 -0.0952 0.3700 0.5188 9.250 1.3004 0.01692 0.01017 -0.0935 0.3661 0.5221 9.500 1.3170 0.01722 0.01048 -0.0915 0.3624 0.5249 9.750 1.3339 0.01762 0.01089 -0.0897 0.3584 0.5275 10.000 1.3535 0.01799 0.01132 -0.0885 0.3539 0.5307 10.250 1.3725 0.01840 0.01179 -0.0872 0.3480 0.5339 10.500 1.3876 0.01896 0.01237 -0.0855 0.3423 0.5373 10.750 1.4032 0.01957 0.01300 -0.0839 0.3378 0.5408 11.000 1.4213 0.02012 0.01361 -0.0828 0.3328 0.5443 11.250 1.4350 0.02089 0.01439 -0.0812 0.3269 0.5473 11.500 1.4456 0.02188 0.01541 -0.0795 0.3212 0.5502 11.750 1.4605 0.02275 0.01635 -0.0785 0.3146 0.5536 12.000 1.4682 0.02410 0.01772 -0.0770 0.3072 0.5568 12.250 1.4779 0.02544 0.01911 -0.0758 0.3001 0.5602 12.500 1.4830 0.02719 0.02088 -0.0745 0.2916 0.5635 12.750 1.4875 0.02908 0.02279 -0.0733 0.2835 0.5668 13.000 1.4864 0.03147 0.02518 -0.0720 0.2742 0.5696 13.250 1.4858 0.03390 0.02765 -0.0709 0.2650 0.5728 13.500 1.4772 0.03708 0.03085 -0.0697 0.2558 0.5759 13.750 1.4718 0.04003 0.03383 -0.0686 0.2457 0.5791 14.000 1.4601 0.04360 0.03743 -0.0675 0.2363 0.5820 14.250 1.4459 0.04754 0.04138 -0.0665 0.2261 0.5847 14.500 1.4334 0.05143 0.04528 -0.0657 0.2156 0.5874 14.750 1.4180 0.05572 0.04958 -0.0650 0.2061 0.5898 15.000 1.4022 0.06014 0.05400 -0.0644 0.1963 0.5920 15.250 1.3911 0.06416 0.05804 -0.0641 0.1872 0.5945 15.500 1.3775 0.06854 0.06243 -0.0638 0.1783 0.5974 15.750 1.3652 0.07284 0.06675 -0.0637 0.1695 0.6005 16.000 1.3551 0.07697 0.07091 -0.0636 0.1617 0.6038 16.250 1.3439 0.08125 0.07518 -0.0637 0.1538 0.6071 16.500 1.3363 0.08522 0.07919 -0.0638 0.1462 0.6104 16.750 1.3292 0.08911 0.08307 -0.0640 0.1393 0.6135 17.000 1.3211 0.09321 0.08718 -0.0644 0.1322 0.6161 17.250 1.3172 0.09683 0.09083 -0.0647 0.1258 0.6194