XFOIL Version 6.94 Calculated polar for: AH 79-K-132/20 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 0.3400 0.01110 0.00661 -0.0653 0.7278 0.9056 0.500 0.3805 0.01113 0.00663 -0.0608 0.7223 0.9302 1.000 0.4307 0.01087 0.00632 -0.0590 0.7172 0.9468 1.500 0.4903 0.01063 0.00604 -0.0596 0.7114 0.9576 2.000 0.5593 0.01029 0.00565 -0.0625 0.7057 0.9610 2.500 0.6191 0.01004 0.00541 -0.0637 0.6980 0.9663 3.000 0.6834 0.00970 0.00507 -0.0658 0.6908 0.9697 3.500 0.7522 0.00938 0.00476 -0.0688 0.6813 0.9723 4.000 0.8131 0.00914 0.00458 -0.0703 0.6682 0.9762 4.500 0.8756 0.00896 0.00445 -0.0721 0.6523 0.9798 5.000 0.9410 0.00886 0.00437 -0.0746 0.6294 0.9830 5.500 0.9951 0.00894 0.00440 -0.0747 0.5966 0.9876 6.000 1.0549 0.00927 0.00468 -0.0764 0.5597 0.9908 6.500 1.1079 0.00975 0.00513 -0.0767 0.5221 0.9953 7.000 1.1465 0.01059 0.00580 -0.0745 0.4649 1.0000 7.500 1.1372 0.01146 0.00647 -0.0627 0.4107 1.0000 8.000 1.1315 0.01284 0.00753 -0.0525 0.3429 1.0000 8.500 1.1264 0.01536 0.00961 -0.0449 0.2580 1.0000 9.000 1.1262 0.01865 0.01241 -0.0398 0.1702 1.0000 9.500 1.1187 0.02250 0.01563 -0.0341 0.0692 1.0000 10.000 1.1129 0.02657 0.01930 -0.0288 0.0149 1.0000 10.500 1.1265 0.02951 0.02237 -0.0257 0.0115 1.0000 11.000 1.1404 0.03256 0.02558 -0.0228 0.0098 1.0000 11.500 1.1487 0.03617 0.02937 -0.0200 0.0092 1.0000 12.000 1.1550 0.04020 0.03356 -0.0176 0.0089 1.0000 12.500 1.1503 0.04553 0.03906 -0.0147 0.0085 1.0000 13.000 1.1619 0.04957 0.04329 -0.0131 0.0080 1.0000 13.500 1.1724 0.05383 0.04774 -0.0114 0.0078 1.0000 14.000 1.1847 0.05808 0.05221 -0.0101 0.0074 1.0000 14.500 1.1964 0.06256 0.05693 -0.0085 0.0073 1.0000 15.000 1.2040 0.06781 0.06247 -0.0075 0.0071 1.0000 15.500 1.2042 0.07438 0.06943 -0.0068 0.0072 1.0000 16.000 1.1930 0.08287 0.07835 -0.0073 0.0075 1.0000 16.500 1.1722 0.09323 0.08912 -0.0095 0.0077 1.0000 17.000 1.1446 0.10526 0.10154 -0.0136 0.0079 1.0000 17.500 1.1138 0.11866 0.11529 -0.0196 0.0081 1.0000 18.000 1.1064 0.12836 0.12520 -0.0243 0.0087 1.0000