XFOIL Version 6.96 Calculated polar for: WORTMANN FX 79-K-144/17 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.7383 0.10162 0.09918 -0.0348 0.7928 0.0078 -14.750 -0.9222 0.05615 0.05319 -0.0647 0.7931 0.0073 -14.500 -0.9499 0.04822 0.04503 -0.0701 0.7927 0.0073 -14.250 -0.9685 0.04317 0.03978 -0.0720 0.7924 0.0072 -14.000 -0.9812 0.03941 0.03583 -0.0721 0.7922 0.0073 -13.750 -0.9889 0.03643 0.03267 -0.0713 0.7920 0.0073 -13.500 -0.9924 0.03395 0.03001 -0.0702 0.7917 0.0073 -13.250 -0.9926 0.03178 0.02768 -0.0688 0.7913 0.0073 -13.000 -0.9894 0.02987 0.02560 -0.0674 0.7906 0.0074 -12.750 -0.9829 0.02823 0.02380 -0.0661 0.7899 0.0074 -12.500 -0.9762 0.02694 0.02236 -0.0642 0.7891 0.0075 -12.250 -0.9648 0.02574 0.02102 -0.0628 0.7885 0.0076 -12.000 -0.9499 0.02461 0.01976 -0.0619 0.7879 0.0077 -11.750 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0.0260 0.8846 7.750 1.0700 0.01634 0.00964 -0.0600 0.0238 0.8852 8.000 1.0897 0.01694 0.01025 -0.0596 0.0213 0.8859 8.250 1.1096 0.01762 0.01094 -0.0593 0.0186 0.8865 8.500 1.1293 0.01830 0.01163 -0.0591 0.0156 0.8870 8.750 1.1482 0.01898 0.01231 -0.0587 0.0127 0.8880 9.000 1.1657 0.01971 0.01304 -0.0580 0.0108 0.8891 9.250 1.1827 0.02047 0.01381 -0.0573 0.0100 0.8900 9.500 1.1992 0.02124 0.01461 -0.0565 0.0095 0.8909 9.750 1.2145 0.02210 0.01551 -0.0555 0.0090 0.8918 10.000 1.2289 0.02301 0.01646 -0.0545 0.0087 0.8927 10.250 1.2437 0.02389 0.01739 -0.0535 0.0086 0.8936 10.500 1.2574 0.02484 0.01841 -0.0524 0.0084 0.8946 10.750 1.2705 0.02584 0.01946 -0.0512 0.0083 0.8956 11.000 1.2831 0.02688 0.02056 -0.0501 0.0081 0.8967 11.250 1.2944 0.02802 0.02176 -0.0489 0.0080 0.8977 11.500 1.3053 0.02920 0.02300 -0.0476 0.0078 0.8988 11.750 1.3155 0.03045 0.02431 -0.0463 0.0077 0.8998 12.000 1.3245 0.03180 0.02572 -0.0450 0.0076 0.9008 12.250 1.3329 0.03320 0.02719 -0.0437 0.0074 0.9017 12.500 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0.08506 0.08133 -0.0271 0.0063 0.9816 17.500 1.3397 0.08946 0.08587 -0.0281 0.0063 1.0000 17.750 1.3326 0.09411 0.09066 -0.0293 0.0063 1.0000 18.000 1.3236 0.09912 0.09580 -0.0307 0.0063 1.0000 18.250 1.3138 0.10440 0.10123 -0.0325 0.0063 1.0000 18.500 1.3024 0.11009 0.10707 -0.0345 0.0063 1.0000 18.750 1.2908 0.11604 0.11315 -0.0371 0.0063 1.0000 19.000 1.2777 0.12237 0.11963 -0.0399 0.0063 1.0000 19.250 1.2628 0.12923 0.12665 -0.0433 0.0063 1.0000