XFOIL Version 6.94 Calculated polar for: E178 (8.69%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2670 0.00777 0.00244 -0.0487 0.6937 1.0000 0.500 0.3191 0.00795 0.00242 -0.0478 0.6816 1.0000 1.000 0.3719 0.00811 0.00249 -0.0472 0.6689 1.0000 1.500 0.4252 0.00831 0.00261 -0.0466 0.6566 1.0000 2.000 0.4786 0.00850 0.00274 -0.0460 0.6435 1.0000 2.500 0.5320 0.00868 0.00287 -0.0454 0.6287 1.0000 3.000 0.5857 0.00884 0.00304 -0.0449 0.6129 1.0000 3.500 0.6394 0.00898 0.00320 -0.0443 0.5952 1.0000 4.000 0.6931 0.00912 0.00340 -0.0437 0.5759 1.0000 4.500 0.7466 0.00927 0.00359 -0.0431 0.5539 1.0000 5.000 0.7997 0.00942 0.00382 -0.0424 0.5254 1.0000 5.500 0.8523 0.00964 0.00419 -0.0417 0.4871 1.0000 6.000 0.9027 0.01011 0.00461 -0.0407 0.4202 1.0000 6.500 0.9377 0.01252 0.00586 -0.0385 0.2023 1.0000 7.000 0.9759 0.01469 0.00741 -0.0369 0.0876 1.0000 7.500 1.0054 0.01791 0.01027 -0.0335 0.0172 1.0000 8.000 1.0349 0.02069 0.01341 -0.0299 0.0142 1.0000 8.500 1.0673 0.02287 0.01577 -0.0271 0.0115 1.0000 9.000 1.0930 0.02590 0.01902 -0.0234 0.0106 1.0000 9.500 1.1168 0.03031 0.02372 -0.0198 0.0097 1.0000 10.000 1.1411 0.03509 0.02895 -0.0164 0.0097 1.0000 10.500 1.1508 0.04054 0.03502 -0.0118 0.0103 1.0000 11.000 1.1268 0.04969 0.04505 -0.0067 0.0118 1.0000 11.500 1.0926 0.05877 0.05466 -0.0053 0.0127 1.0000 12.000 1.0570 0.06883 0.06512 -0.0075 0.0133 1.0000 12.500 1.0189 0.08084 0.07747 -0.0130 0.0135 1.0000 13.000 0.9799 0.09540 0.09232 -0.0219 0.0136 1.0000 13.500 0.9408 0.11427 0.11142 -0.0345 0.0136 1.0000 14.000 0.9030 0.13892 0.13615 -0.0485 0.0142 1.0000 14.500 0.7276 0.14098 0.13861 -0.0522 0.0144 1.0000 15.500 0.7105 0.16935 0.16696 -0.0652 0.0276 1.0000 16.000 0.7184 0.17681 0.17444 -0.0686 0.0265 1.0000 16.500 0.7291 0.18429 0.18195 -0.0710 0.0249 1.0000 17.000 0.7301 0.19576 0.19339 -0.0759 0.0242 1.0000 17.500 0.7369 0.20405 0.20168 -0.0802 0.0240 1.0000 18.000 0.7426 0.21149 0.20913 -0.0850 0.0232 1.0000 18.500 0.7482 0.21970 0.21735 -0.0900 0.0209 1.0000 19.000 0.7570 0.22772 0.22539 -0.0937 0.0190 1.0000 19.500 0.7667 0.23539 0.23308 -0.0972 0.0176 1.0000 20.000 0.7775 0.24285 0.24057 -0.1003 0.0165 1.0000 20.500 0.7907 0.25385 0.25157 -0.1022 0.0152 1.0000 21.000 0.7988 0.26236 0.26013 -0.1060 0.0151 1.0000 21.500 0.8043 0.27013 0.26791 -0.1105 0.0149 1.0000 22.000 0.8105 0.27817 0.27597 -0.1155 0.0137 1.0000 22.500 0.8192 0.28698 0.28480 -0.1192 0.0118 1.0000 23.000 0.8283 0.29564 0.29348 -0.1227 0.0106 1.0000 23.500 0.8371 0.30392 0.30179 -0.1260 0.0099 1.0000 24.000 0.8460 0.31223 0.31013 -0.1290 0.0095 1.0000 24.500 0.8567 0.32416 0.32206 -0.1314 0.0090 1.0000 25.000 0.8638 0.33333 0.33126 -0.1351 0.0090 1.0000 25.500 0.8701 0.34243 0.34040 -0.1389 0.0089 1.0000 26.000 0.8757 0.35150 0.34950 -0.1428 0.0088 1.0000 26.500 0.8819 0.36077 0.35879 -0.1466 0.0087 1.0000 27.000 0.8883 0.36995 0.36800 -0.1503 0.0086 1.0000 27.500 0.8947 0.37913 0.37720 -0.1539 0.0084 1.0000 28.000 0.9015 0.38892 0.38702 -0.1574 0.0078 1.0000 28.500 0.9074 0.39861 0.39673 -0.1608 0.0074 1.0000 29.000 0.9129 0.40813 0.40629 -0.1641 0.0070 1.0000 29.500 0.9183 0.41796 0.41614 -0.1675 0.0066 1.0000 30.000 0.9230 0.42744 0.42568 -0.1707 0.0063 1.0000 30.500 0.9277 0.43727 0.43553 -0.1741 0.0060 1.0000 31.000 0.9320 0.44697 0.44527 -0.1773 0.0057 1.0000 31.500 0.9354 0.45645 0.45478 -0.1805 0.0053 1.0000 32.000 0.9389 0.46592 0.46428 -0.1837 0.0051 1.0000 32.500 0.9419 0.47551 0.47390 -0.1868 0.0046 1.0000 33.000 0.9447 0.48565 0.48409 -0.1896 0.0044 1.0000 34.500 0.9513 0.51899 0.51750 -0.1987 0.0042 1.0000 35.000 0.9523 0.52860 0.52713 -0.2018 0.0042 1.0000