XFOIL Version 6.96 Calculated polar for: AH 79-K-132/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7458 0.03832 0.03508 -0.1118 0.7542 0.0045 -13.500 -0.7743 0.03397 0.03049 -0.1102 0.7532 0.0044 -13.250 -0.7773 0.03204 0.02844 -0.1083 0.7524 0.0045 -13.000 -0.7858 0.02992 0.02615 -0.1054 0.7514 0.0046 -12.750 -0.7851 0.02856 0.02470 -0.1027 0.7506 0.0047 -12.500 -0.7842 0.02735 0.02338 -0.0995 0.7498 0.0048 -12.250 -0.7784 0.02610 0.02199 -0.0971 0.7490 0.0048 -12.000 -0.7692 0.02485 0.02062 -0.0952 0.7480 0.0049 -11.750 -0.7549 0.02395 0.01962 -0.0937 0.7471 0.0051 -11.500 -0.7402 0.02301 0.01857 -0.0923 0.7463 0.0052 -11.250 -0.7231 0.02223 0.01769 -0.0912 0.7454 0.0053 -11.000 -0.7056 0.02142 0.01677 -0.0900 0.7446 0.0055 -10.750 -0.6884 0.02051 0.01574 -0.0889 0.7438 0.0056 -10.500 -0.6682 0.01988 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0.01058 0.00423 -0.0788 0.7251 0.0118 -5.500 -0.1921 0.01033 0.00395 -0.0787 0.7239 0.0128 -5.250 -0.1657 0.01011 0.00372 -0.0785 0.7227 0.0138 -5.000 -0.1390 0.00990 0.00349 -0.0784 0.7215 0.0148 -4.750 -0.1126 0.00966 0.00327 -0.0783 0.7200 0.0184 -4.500 -0.0859 0.00946 0.00309 -0.0782 0.7183 0.0228 -4.250 -0.0591 0.00927 0.00293 -0.0782 0.7167 0.0285 -4.000 -0.0319 0.00912 0.00277 -0.0781 0.7152 0.0311 -3.750 -0.0048 0.00896 0.00261 -0.0781 0.7137 0.0356 -3.500 0.0225 0.00882 0.00247 -0.0781 0.7122 0.0394 -3.250 0.0499 0.00870 0.00233 -0.0782 0.7108 0.0437 -3.000 0.0772 0.00857 0.00223 -0.0782 0.7093 0.0497 -2.750 0.1047 0.00845 0.00213 -0.0782 0.7075 0.0549 -2.500 0.1321 0.00832 0.00204 -0.0783 0.7054 0.0639 -2.250 0.1598 0.00822 0.00194 -0.0784 0.7031 0.0697 -2.000 0.1873 0.00810 0.00185 -0.0784 0.7009 0.0767 -1.750 0.2149 0.00800 0.00174 -0.0785 0.6987 0.0833 -1.500 0.2423 0.00788 0.00165 -0.0786 0.6965 0.0964 -1.250 0.2695 0.00772 0.00159 -0.0786 0.6940 0.1234 -1.000 0.2965 0.00755 0.00154 -0.0786 0.6910 0.1603 -0.750 0.3231 0.00734 0.00147 -0.0786 0.6878 0.2111 -0.250 0.3662 0.00600 0.00128 -0.0771 0.6818 0.5943 0.000 0.3878 0.00554 0.00128 -0.0759 0.6778 0.7316 0.250 0.4132 0.00543 0.00132 -0.0754 0.6736 0.7848 0.500 0.4395 0.00543 0.00137 -0.0750 0.6694 0.8194 0.750 0.4665 0.00548 0.00147 -0.0748 0.6646 0.8440 1.000 0.4933 0.00556 0.00155 -0.0746 0.6590 0.8588 1.250 0.5207 0.00561 0.00158 -0.0745 0.6536 0.8643 1.500 0.5485 0.00565 0.00161 -0.0746 0.6463 0.8670 1.750 0.5760 0.00570 0.00163 -0.0746 0.6389 0.8697 2.000 0.6033 0.00576 0.00166 -0.0746 0.6297 0.8726 2.250 0.6304 0.00583 0.00169 -0.0746 0.6191 0.8752 2.500 0.6561 0.00594 0.00176 -0.0743 0.6065 0.8790 2.750 0.6818 0.00607 0.00185 -0.0739 0.5935 0.8823 3.000 0.7075 0.00620 0.00193 -0.0737 0.5800 0.8847 3.250 0.7332 0.00634 0.00202 -0.0734 0.5658 0.8865 3.500 0.7584 0.00650 0.00212 -0.0731 0.5497 0.8881 3.750 0.7819 0.00674 0.00227 -0.0724 0.5272 0.8898 4.000 0.8055 0.00694 0.00241 -0.0718 0.5076 0.8915 4.250 0.8286 0.00717 0.00258 -0.0711 0.4883 0.8933 4.500 0.8505 0.00745 0.00277 -0.0701 0.4628 0.8952 4.750 0.8726 0.00773 0.00297 -0.0693 0.4406 0.8968 5.000 0.8943 0.00802 0.00317 -0.0684 0.4185 0.8984 5.250 0.9159 0.00830 0.00338 -0.0674 0.3974 0.9000 5.500 0.9365 0.00863 0.00361 -0.0663 0.3752 0.9017 5.750 0.9555 0.00900 0.00388 -0.0650 0.3489 0.9033 6.000 0.9748 0.00932 0.00414 -0.0636 0.3285 0.9049 6.250 0.9939 0.00963 0.00440 -0.0623 0.3096 0.9065 6.500 1.0080 0.01010 0.00475 -0.0600 0.2796 0.9084 6.750 1.0172 0.01071 0.00518 -0.0569 0.2436 0.9107 7.000 1.0143 0.01148 0.00572 -0.0515 0.1972 0.9141 7.500 1.0075 0.01324 0.00711 -0.0413 0.1199 0.9218 7.750 1.0042 0.01434 0.00805 -0.0370 0.0862 0.9266 8.250 1.0164 0.01627 0.00982 -0.0320 0.0440 0.9353 8.500 1.0301 0.01693 0.01049 -0.0306 0.0372 0.9393 8.750 1.0424 0.01772 0.01125 -0.0291 0.0267 0.9437 9.000 1.0536 0.01875 0.01219 -0.0278 0.0118 0.9494 9.250 1.0721 0.01957 0.01303 -0.0277 0.0076 0.9551 9.500 1.0946 0.02041 0.01391 -0.0284 0.0052 0.9606 9.750 1.1208 0.02126 0.01480 -0.0299 0.0043 0.9651 10.000 1.1462 0.02226 0.01583 -0.0315 0.0034 0.9691 10.500 1.1923 0.02415 0.01782 -0.0335 0.0030 1.0000 10.750 1.2063 0.02514 0.01885 -0.0327 0.0028 1.0000 11.000 1.2194 0.02617 0.01992 -0.0319 0.0026 1.0000 11.250 1.2320 0.02725 0.02106 -0.0311 0.0025 1.0000 11.500 1.2439 0.02838 0.02224 -0.0302 0.0022 1.0000 11.750 1.2545 0.02962 0.02353 -0.0292 0.0021 1.0000 12.000 1.2597 0.03129 0.02529 -0.0278 0.0020 1.0000 12.250 1.2664 0.03287 0.02693 -0.0267 0.0019 1.0000 12.500 1.2787 0.03401 0.02812 -0.0260 0.0019 1.0000 12.750 1.2855 0.03564 0.02983 -0.0250 0.0019 1.0000 13.000 1.2901 0.03756 0.03183 -0.0239 0.0019 1.0000 13.250 1.2996 0.03909 0.03341 -0.0233 0.0019 1.0000 13.500 1.3089 0.04064 0.03502 -0.0227 0.0018 1.0000 13.750 1.3128 0.04274 0.03723 -0.0219 0.0018 1.0000 14.000 1.3195 0.04464 0.03920 -0.0214 0.0018 1.0000 14.250 1.3246 0.04672 0.04135 -0.0208 0.0018 1.0000 14.500 1.3270 0.04910 0.04382 -0.0202 0.0017 1.0000 14.750 1.3284 0.05165 0.04647 -0.0196 0.0017 1.0000 15.000 1.3331 0.05391 0.04880 -0.0193 0.0017 1.0000 15.250 1.3309 0.05695 0.05196 -0.0189 0.0017 1.0000 15.500 1.3314 0.05973 0.05483 -0.0186 0.0017 1.0000 15.750 1.3319 0.06258 0.05776 -0.0185 0.0017 1.0000 16.000 1.3309 0.06567 0.06095 -0.0185 0.0016 1.0000 16.250 1.3302 0.06878 0.06415 -0.0186 0.0016 1.0000 16.500 1.3287 0.07200 0.06746 -0.0187 0.0016 1.0000 16.750 1.3268 0.07534 0.07090 -0.0190 0.0015 1.0000 17.000 1.3225 0.07904 0.07470 -0.0194 0.0015 1.0000 17.250 1.3167 0.08301 0.07878 -0.0199 0.0016 1.0000 17.500 1.3125 0.08683 0.08271 -0.0205 0.0015 1.0000 17.750 1.3060 0.09101 0.08699 -0.0213 0.0015 1.0000 18.000 1.3014 0.09502 0.09110 -0.0222 0.0015 1.0000 18.250 1.2952 0.09934 0.09552 -0.0233 0.0014 1.0000 18.500 1.2803 0.10500 0.10133 -0.0247 0.0015 1.0000 18.750 1.2761 0.10919 0.10560 -0.0261 0.0015 1.0000