XFOIL Version 6.94 Calculated polar for: E214 (11.1%) 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 0.6021 0.00732 0.00230 -0.1428 0.7625 0.6939 0.500 0.6556 0.00746 0.00236 -0.1421 0.7378 0.7222 1.000 0.7079 0.00759 0.00247 -0.1412 0.7134 0.7532 1.500 0.7595 0.00773 0.00261 -0.1401 0.6907 0.7886 2.000 0.8089 0.00782 0.00277 -0.1386 0.6674 0.8314 2.500 0.8516 0.00786 0.00292 -0.1354 0.6442 0.9013 3.000 0.9036 0.00797 0.00301 -0.1345 0.6206 1.0000 3.500 0.9561 0.00828 0.00325 -0.1339 0.5951 1.0000 4.000 1.0070 0.00862 0.00351 -0.1330 0.5674 1.0000 4.500 1.0567 0.00902 0.00384 -0.1318 0.5396 1.0000 5.000 1.1049 0.00946 0.00420 -0.1304 0.5077 1.0000 5.500 1.1517 0.00995 0.00462 -0.1287 0.4719 1.0000 6.000 1.1966 0.01053 0.00513 -0.1267 0.4313 1.0000 6.500 1.2377 0.01130 0.00574 -0.1240 0.3807 1.0000 7.000 1.2744 0.01231 0.00651 -0.1207 0.3184 1.0000 7.500 1.3059 0.01357 0.00749 -0.1165 0.2513 1.0000 8.000 1.3300 0.01520 0.00872 -0.1113 0.1784 1.0000 8.500 1.3549 0.01683 0.01006 -0.1064 0.1226 1.0000 9.000 1.3795 0.01847 0.01154 -0.1016 0.0848 1.0000 9.500 1.4031 0.02017 0.01316 -0.0968 0.0588 1.0000 10.000 1.4253 0.02198 0.01493 -0.0922 0.0395 1.0000 10.500 1.4383 0.02452 0.01739 -0.0867 0.0198 1.0000 11.000 1.4432 0.02786 0.02084 -0.0808 0.0121 1.0000 11.500 1.4554 0.03084 0.02406 -0.0764 0.0102 1.0000 12.000 1.4600 0.03471 0.02813 -0.0721 0.0091 1.0000 12.500 1.4480 0.04056 0.03426 -0.0678 0.0083 1.0000 13.000 1.4483 0.04580 0.03977 -0.0654 0.0080 1.0000 13.500 1.4462 0.05179 0.04602 -0.0638 0.0077 1.0000 14.000 1.4436 0.05833 0.05283 -0.0632 0.0073 1.0000 14.500 1.4399 0.06545 0.06021 -0.0634 0.0069 1.0000 15.000 1.4349 0.07323 0.06824 -0.0645 0.0065 1.0000 15.500 1.4263 0.08203 0.07734 -0.0665 0.0063 1.0000 16.000 1.4143 0.09188 0.08747 -0.0695 0.0062 1.0000 16.500 1.4001 0.10264 0.09854 -0.0734 0.0061 1.0000 17.000 1.3835 0.11434 0.11054 -0.0785 0.0060 1.0000 17.500 1.3645 0.12711 0.12365 -0.0849 0.0060 1.0000 18.000 1.3440 0.14080 0.13766 -0.0927 0.0060 1.0000 18.500 1.3210 0.15582 0.15301 -0.1019 0.0060 1.0000 19.000 1.2932 0.17315 0.17069 -0.1132 0.0061 1.0000 19.500 1.2446 0.19887 0.19685 -0.1302 0.0065 1.0000