XFOIL Version 6.96 Calculated polar for: AH 93-W-257 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1309 0.10207 0.09611 -0.0289 1.0000 0.1209 -19.500 -1.1437 0.09704 0.09088 -0.0309 1.0000 0.1233 -19.250 -1.1202 0.09735 0.09134 -0.0305 1.0000 0.1263 -19.000 -1.1112 0.09548 0.08950 -0.0312 1.0000 0.1293 -18.750 -1.1116 0.09228 0.08622 -0.0323 1.0000 0.1325 -18.500 -1.1090 0.08957 0.08345 -0.0332 1.0000 0.1358 -18.250 -1.0926 0.08881 0.08282 -0.0333 1.0000 0.1394 -18.000 -1.0916 0.08586 0.07984 -0.0343 1.0000 0.1435 -17.750 -1.0886 0.08324 0.07719 -0.0350 1.0000 0.1479 -17.500 -1.0775 0.08177 0.07584 -0.0354 1.0000 0.1527 -17.250 -1.0823 0.07811 0.07209 -0.0366 1.0000 0.1581 -17.000 -1.0694 0.07693 0.07106 -0.0367 1.0000 0.1636 -16.750 -1.0728 0.07353 0.06762 -0.0378 1.0000 0.1703 -16.500 -1.0648 0.07173 0.06595 -0.0382 1.0000 0.1771 -16.250 -1.0743 0.06767 0.06181 -0.0394 1.0000 0.1852 -16.000 -1.0639 0.06620 0.06052 -0.0396 1.0000 0.1931 -15.750 -1.0701 0.06268 0.05697 -0.0406 1.0000 0.2020 -15.500 -1.0683 0.06018 0.05455 -0.0412 1.0000 0.2109 -15.250 -1.0642 0.05800 0.05243 -0.0417 1.0000 0.2197 -15.000 -1.0785 0.05373 0.04808 -0.0429 1.0000 0.2293 -14.750 -1.0598 0.05321 0.04773 -0.0429 1.0000 0.2374 -14.500 -1.0725 0.04930 0.04374 -0.0439 1.0000 0.2467 -14.250 -1.0544 0.04870 0.04327 -0.0440 1.0000 0.2545 -14.000 -1.0646 0.04522 0.03972 -0.0448 1.0000 0.2632 -13.750 -1.0436 0.04487 0.03950 -0.0449 1.0000 0.2702 -13.500 -1.0614 0.04088 0.03541 -0.0458 1.0000 0.2788 -13.250 -1.0290 0.04152 0.03622 -0.0459 1.0000 0.2849 -13.000 -1.0481 0.03768 0.03232 -0.0468 1.0000 0.2934 -12.750 -0.9961 0.03836 0.03290 -0.0504 0.8770 0.3002 -12.500 -0.9959 0.03647 0.03078 -0.0504 0.8399 0.3076 -12.250 -0.9928 0.03488 0.02903 -0.0502 0.8172 0.3141 -12.000 -0.9644 0.03534 0.02947 -0.0500 0.7993 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0.01895 -0.0723 0.6061 0.4942 -2.250 0.0101 0.02683 0.01955 -0.0712 0.6033 0.4953 -2.000 0.0375 0.02743 0.02015 -0.0701 0.6009 0.4963 -1.750 0.0646 0.02814 0.02086 -0.0693 0.5984 0.4975 -1.500 0.0914 0.02867 0.02147 -0.0687 0.5959 0.4989 -1.250 0.1322 0.02665 0.01930 -0.0765 0.5929 0.5124 -1.000 0.1578 0.02714 0.01988 -0.0755 0.5898 0.5135 -0.750 0.1838 0.02760 0.02040 -0.0745 0.5867 0.5145 -0.500 0.2102 0.02804 0.02088 -0.0737 0.5838 0.5156 -0.250 0.2369 0.02850 0.02136 -0.0728 0.5814 0.5169 0.000 0.2636 0.02900 0.02188 -0.0720 0.5792 0.5183 0.250 0.2906 0.02952 0.02239 -0.0713 0.5771 0.5200 0.500 0.3190 0.02984 0.02271 -0.0718 0.5748 0.5236 0.750 0.3582 0.02839 0.02123 -0.0780 0.5715 0.5340 1.000 0.3822 0.02892 0.02186 -0.0770 0.5681 0.5353 1.250 0.4069 0.02944 0.02246 -0.0760 0.5651 0.5367 1.500 0.4318 0.02994 0.02302 -0.0750 0.5625 0.5382 1.750 0.4582 0.03029 0.02340 -0.0745 0.5600 0.5403 2.000 0.5072 0.02871 0.02165 -0.0824 0.5577 0.5527 2.250 0.5331 0.02904 0.02199 -0.0815 0.5555 0.5539 2.500 0.5587 0.02962 0.02257 -0.0806 0.5533 0.5552 2.750 0.5787 0.03032 0.02345 -0.0792 0.5501 0.5567 3.000 0.5993 0.03101 0.02428 -0.0781 0.5466 0.5584 3.250 0.6234 0.03143 0.02479 -0.0776 0.5433 0.5609 3.500 0.6559 0.03128 0.02464 -0.0793 0.5403 0.5659 3.750 0.6993 0.03047 0.02373 -0.0844 0.5377 0.5740 4.000 0.7246 0.03075 0.02406 -0.0835 0.5356 0.5755 4.250 0.7504 0.03106 0.02439 -0.0825 0.5337 0.5771 4.500 0.7767 0.03153 0.02486 -0.0818 0.5316 0.5789 4.750 0.7905 0.03245 0.02602 -0.0805 0.5268 0.5815 5.000 0.8146 0.03291 0.02658 -0.0810 0.5227 0.5855 5.250 0.8603 0.03229 0.02589 -0.0866 0.5195 0.5943 5.500 0.8850 0.03241 0.02607 -0.0856 0.5169 0.5959 5.750 0.9114 0.03249 0.02618 -0.0848 0.5148 0.5976 6.000 0.9394 0.03254 0.02625 -0.0842 0.5129 0.5995 6.250 0.9697 0.03270 0.02639 -0.0842 0.5108 0.6020 6.500 0.9734 0.03416 0.02814 -0.0824 0.5041 0.6051 6.750 1.0058 0.03417 0.02819 -0.0845 0.5001 0.6108 7.000 1.0447 0.03372 0.02771 -0.0872 0.4971 0.6163 7.250 1.0745 0.03340 0.02741 -0.0868 0.4948 0.6181 7.500 1.1069 0.03299 0.02699 -0.0866 0.4927 0.6200 7.750 1.1350 0.03300 0.02703 -0.0863 0.4896 0.6222 8.000 1.1365 0.03425 0.02853 -0.0837 0.4825 0.6247 8.250 1.1678 0.03390 0.02822 -0.0844 0.4785 0.6286 8.500 1.2222 0.03276 0.02694 -0.0893 0.4754 0.6361 8.750 1.2622 0.03170 0.02584 -0.0902 0.4727 0.6384 9.000 1.2746 0.03216 0.02646 -0.0881 0.4670 0.6401 9.250 1.2890 0.03233 0.02675 -0.0861 0.4610 0.6420 9.500 1.3231 0.03148 0.02590 -0.0863 0.4567 0.6445 9.750 1.3695 0.03024 0.02453 -0.0881 0.4527 0.6482 10.000 1.3733 0.03095 0.02546 -0.0856 0.4453 0.6520 10.250 1.4116 0.03012 0.02457 -0.0878 0.4384 0.6572 10.500 1.4477 0.02920 0.02357 -0.0885 0.4326 0.6597 10.750 1.4430 0.02991 0.02451 -0.0842 0.4249 0.6614 11.000 1.4632 0.02952 0.02413 -0.0826 0.4182 0.6637 11.250 1.4646 0.02988 0.02458 -0.0789 0.4115 0.6662 11.500 1.4637 0.03080 0.02562 -0.0759 0.4033 0.6691 11.750 1.4834 0.03095 0.02574 -0.0754 0.3952 0.6727 12.000 1.4789 0.03282 0.02773 -0.0740 0.3851 0.6758 12.250 1.4876 0.03420 0.02910 -0.0740 0.3746 0.6791 12.500 1.4899 0.03566 0.03058 -0.0727 0.3636 0.6809 12.750 1.4770 0.03872 0.03377 -0.0713 0.3515 0.6827 13.000 1.4714 0.04127 0.03635 -0.0703 0.3390 0.6847 13.250 1.4667 0.04383 0.03889 -0.0693 0.3255 0.6869 13.500 1.4582 0.04689 0.04192 -0.0686 0.3109 0.6891 13.750 1.4457 0.05053 0.04555 -0.0681 0.2956 0.6912 14.000 1.4345 0.05415 0.04914 -0.0677 0.2798 0.6933 14.250 1.4243 0.05788 0.05280 -0.0677 0.2638 0.6955 14.500 1.4141 0.06180 0.05663 -0.0678 0.2478 0.6977 14.750 1.4041 0.06579 0.06055 -0.0680 0.2323 0.6996 15.000 1.3933 0.06969 0.06440 -0.0679 0.2176 0.7010 15.250 1.3824 0.07371 0.06838 -0.0678 0.2038 0.7025 15.500 1.3722 0.07772 0.07235 -0.0678 0.1905 0.7042 15.750 1.3627 0.08177 0.07635 -0.0680 0.1780 0.7061 16.000 1.3533 0.08590 0.08042 -0.0683 0.1662 0.7080 16.500 1.3381 0.09410 0.08854 -0.0695 0.1440 0.7121 16.750 1.3328 0.09808 0.09248 -0.0703 0.1338 0.7142 17.000 1.3275 0.10213 0.09648 -0.0713 0.1245 0.7163