XFOIL Version 6.94 Calculated polar for: E205 (10.48%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3356 0.00728 0.00224 -0.0604 0.5976 0.9931 0.500 0.4097 0.00735 0.00212 -0.0645 0.5838 1.0000 1.000 0.4589 0.00746 0.00211 -0.0632 0.5713 1.0000 1.500 0.5087 0.00757 0.00216 -0.0619 0.5587 1.0000 2.000 0.5587 0.00773 0.00226 -0.0607 0.5467 1.0000 2.500 0.6087 0.00793 0.00238 -0.0595 0.5348 1.0000 3.000 0.6587 0.00812 0.00253 -0.0582 0.5214 1.0000 3.500 0.7087 0.00828 0.00269 -0.0570 0.5069 1.0000 4.000 0.7586 0.00847 0.00289 -0.0558 0.4918 1.0000 4.500 0.8083 0.00868 0.00312 -0.0545 0.4756 1.0000 5.000 0.8577 0.00891 0.00337 -0.0532 0.4581 1.0000 5.500 0.9066 0.00918 0.00368 -0.0517 0.4386 1.0000 6.000 0.9551 0.00944 0.00400 -0.0503 0.4128 1.0000 6.500 1.0003 0.00990 0.00436 -0.0483 0.3657 1.0000 7.000 1.0421 0.01068 0.00496 -0.0460 0.3015 1.0000 7.500 1.0762 0.01214 0.00596 -0.0427 0.2078 1.0000 8.000 1.1073 0.01384 0.00724 -0.0391 0.1273 1.0000 8.500 1.1368 0.01556 0.00865 -0.0353 0.0678 1.0000 9.000 1.1557 0.01785 0.01060 -0.0300 0.0178 1.0000 9.500 1.1777 0.01961 0.01249 -0.0250 0.0128 1.0000 10.000 1.1917 0.02133 0.01440 -0.0189 0.0116 1.0000 10.500 1.2009 0.02359 0.01682 -0.0134 0.0105 1.0000 11.000 1.2014 0.02690 0.02036 -0.0086 0.0098 1.0000 11.500 1.1923 0.03178 0.02549 -0.0052 0.0092 1.0000 12.000 1.1937 0.03638 0.03030 -0.0033 0.0090 1.0000 12.500 1.1980 0.04103 0.03517 -0.0020 0.0088 1.0000 13.000 1.2015 0.04598 0.04035 -0.0011 0.0086 1.0000 13.500 1.2026 0.05142 0.04604 -0.0005 0.0085 1.0000 14.000 1.2010 0.05750 0.05240 -0.0003 0.0084 1.0000 14.500 1.1954 0.06449 0.05970 -0.0009 0.0083 1.0000 15.000 1.1844 0.07275 0.06832 -0.0027 0.0082 1.0000 15.500 1.1669 0.08261 0.07852 -0.0060 0.0082 1.0000 16.000 1.1441 0.09415 0.09041 -0.0109 0.0083 1.0000 16.500 1.1145 0.10800 0.10461 -0.0179 0.0084 1.0000 17.000 1.0813 0.12392 0.12085 -0.0268 0.0084 1.0000 17.500 1.0456 0.14195 0.13915 -0.0374 0.0086 1.0000 18.000 1.0062 0.16310 0.16056 -0.0501 0.0088 1.0000 18.500 0.9727 0.18519 0.18280 -0.0622 0.0093 1.0000