XFOIL Version 6.96 Calculated polar for: WORTMANN FX 057-816 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -0.8643 0.04544 0.04152 -0.0879 0.5915 0.0119 -15.000 -0.8898 0.04041 0.03632 -0.0896 0.5911 0.0119 -14.750 -0.9058 0.03707 0.03282 -0.0892 0.5906 0.0119 -14.500 -0.9144 0.03463 0.03025 -0.0879 0.5901 0.0120 -14.250 -0.9157 0.03286 0.02837 -0.0865 0.5895 0.0122 -14.000 -0.9163 0.03123 0.02661 -0.0847 0.5889 0.0124 -13.750 -0.9164 0.02969 0.02495 -0.0826 0.5882 0.0125 -13.500 -0.9132 0.02843 0.02357 -0.0804 0.5875 0.0127 -13.250 -0.9096 0.02733 0.02235 -0.0778 0.5868 0.0128 -13.000 -0.9056 0.02637 0.02126 -0.0751 0.5858 0.0130 -12.750 -0.8934 0.02550 0.02027 -0.0735 0.5848 0.0131 -12.500 -0.8772 0.02473 0.01940 -0.0722 0.5845 0.0132 -12.250 -0.8677 0.02332 0.01782 -0.0704 0.5842 0.0135 -12.000 -0.8545 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0.8737 7.250 1.2542 0.00908 0.00508 -0.0771 0.5199 0.8746 7.500 1.2835 0.00890 0.00492 -0.0776 0.5146 0.8755 7.750 1.3121 0.00884 0.00489 -0.0780 0.5094 0.8764 8.000 1.3406 0.00878 0.00489 -0.0785 0.5003 0.8774 8.250 1.3680 0.00878 0.00487 -0.0787 0.4836 0.8786 8.500 1.3859 0.00945 0.00528 -0.0776 0.4258 0.8801 8.750 1.3689 0.01240 0.00761 -0.0721 0.3097 0.8825 9.000 1.3650 0.01408 0.00910 -0.0683 0.2690 0.8844 9.250 1.3576 0.01545 0.01043 -0.0640 0.2491 0.8875 9.500 1.3348 0.01837 0.01344 -0.0598 0.2400 0.8919 9.750 1.3119 0.02200 0.01712 -0.0568 0.2320 0.8963 10.000 1.2921 0.02494 0.02005 -0.0533 0.2207 0.9007 10.250 1.2766 0.02752 0.02263 -0.0502 0.2089 0.9054 10.500 1.2616 0.03013 0.02520 -0.0474 0.1918 0.9102 10.750 1.2457 0.03293 0.02791 -0.0447 0.1712 0.9153 11.000 1.2316 0.03559 0.03045 -0.0422 0.1440 0.9223 11.250 1.2196 0.03840 0.03313 -0.0401 0.1165 0.9316 11.500 1.2210 0.04033 0.03504 -0.0390 0.1002 0.9506 11.750 1.2331 0.04226 0.03694 -0.0401 0.0872 1.0000 12.000 1.2400 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0.07686 -0.0383 0.0130 1.0000 17.000 1.3826 0.08495 0.07978 -0.0388 0.0125 1.0000 17.250 1.3843 0.08802 0.08291 -0.0393 0.0121 1.0000