XFOIL Version 6.96 Calculated polar for: FX 78-K-140/20 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.1116 0.08256 0.07996 -0.0730 0.7227 0.0080 -10.500 -0.1146 0.07772 0.07515 -0.0747 0.7222 0.0092 -10.250 -0.1135 0.07409 0.07152 -0.0760 0.7216 0.0080 -10.000 -0.1162 0.06961 0.06706 -0.0775 0.7210 0.0083 -9.750 -0.2121 0.07915 0.07642 -0.0812 0.7236 0.0058 -9.500 -0.2232 0.07204 0.06937 -0.0857 0.7230 0.0060 -8.500 -0.4699 0.02151 0.01709 -0.0774 0.7178 0.0045 -8.250 -0.4272 0.02418 0.02013 -0.0800 0.7168 0.0051 -8.000 -0.4364 0.01923 0.01445 -0.0742 0.7156 0.0048 -7.750 -0.3989 0.02130 0.01681 -0.0763 0.7146 0.0056 -7.500 -0.3861 0.01936 0.01456 -0.0739 0.7136 0.0058 -7.250 -0.3683 0.01806 0.01302 -0.0722 0.7127 0.0062 -7.000 -0.3462 0.01748 0.01231 -0.0714 0.7117 0.0063 -6.750 -0.3329 0.01524 0.00969 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3.000 0.7431 0.00668 0.00295 -0.0755 0.6613 0.9747 3.250 0.7736 0.00669 0.00296 -0.0764 0.6594 0.9776 3.500 0.8037 0.00671 0.00297 -0.0772 0.6571 0.9801 3.750 0.8383 0.00676 0.00304 -0.0791 0.6552 0.9810 4.000 0.8725 0.00678 0.00311 -0.0808 0.6528 0.9822 4.250 0.9062 0.00679 0.00318 -0.0825 0.6502 0.9837 4.500 0.9391 0.00679 0.00321 -0.0840 0.6476 0.9855 4.750 0.9708 0.00677 0.00317 -0.0851 0.6428 0.9877 5.000 1.0020 0.00677 0.00325 -0.0862 0.6378 0.9899 5.250 1.0364 0.00673 0.00324 -0.0880 0.6309 0.9911 5.500 1.0697 0.00669 0.00320 -0.0896 0.6153 0.9927 5.750 1.1016 0.00678 0.00326 -0.0909 0.5896 0.9947 6.000 1.1235 0.00791 0.00389 -0.0912 0.4867 0.9985 6.250 1.1309 0.00932 0.00487 -0.0888 0.4027 1.0000 6.500 1.1203 0.01052 0.00578 -0.0827 0.3456 1.0000 6.750 1.0956 0.01196 0.00698 -0.0743 0.2973 1.0000 7.000 1.0600 0.01373 0.00857 -0.0646 0.2598 1.0000 7.250 1.0488 0.01531 0.00996 -0.0594 0.2203 1.0000 7.500 1.0246 0.01784 0.01205 -0.0532 0.1441 1.0000 7.750 1.0215 0.01947 0.01345 -0.0499 0.0990 1.0000 8.000 1.0045 0.02201 0.01558 -0.0452 0.0222 1.0000 8.250 1.0099 0.02333 0.01685 -0.0429 0.0078 1.0000 8.500 1.0214 0.02431 0.01788 -0.0415 0.0070 1.0000 8.750 1.0316 0.02538 0.01900 -0.0401 0.0056 1.0000 9.000 1.0478 0.02609 0.01973 -0.0392 0.0065 1.0000 9.250 1.0489 0.02785 0.02163 -0.0367 0.0056 1.0000 9.500 1.0662 0.02854 0.02232 -0.0361 0.0050 1.0000 9.750 1.0786 0.02957 0.02339 -0.0351 0.0045 1.0000 10.000 1.0876 0.03089 0.02474 -0.0338 0.0038 1.0000 10.250 1.0959 0.03231 0.02629 -0.0323 0.0044 1.0000 10.500 1.1027 0.03387 0.02787 -0.0309 0.0037 1.0000 10.750 1.1041 0.03586 0.02995 -0.0290 0.0035 1.0000 11.000 1.1137 0.03727 0.03142 -0.0278 0.0036 1.0000 11.250 1.1185 0.03907 0.03330 -0.0262 0.0036 1.0000 11.500 1.1297 0.04036 0.03465 -0.0253 0.0038 1.0000 11.750 1.1336 0.04223 0.03658 -0.0238 0.0036 1.0000 12.000 1.1369 0.04412 0.03857 -0.0217 0.0037 1.0000 12.250 1.1477 0.04546 0.03998 -0.0207 0.0038 1.0000 12.500 1.1584 0.04680 0.04139 -0.0196 0.0038 1.0000 12.750 1.1666 0.04829 0.04292 -0.0181 0.0036 1.0000 13.000 1.1800 0.04935 0.04405 -0.0157 0.0033 1.0000 13.250 1.1916 0.05077 0.04557 -0.0147 0.0033 1.0000