XFOIL Version 6.94 Calculated polar for: AH21 9% version (Andrew Hollom) 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 0.2027 0.00728 0.00357 -0.0551 0.9441 0.9342 1.000 0.3975 0.00629 0.00268 -0.0721 0.9296 1.0000 1.500 0.4551 0.00588 0.00227 -0.0718 0.9034 1.0000 2.000 0.5175 0.00560 0.00193 -0.0725 0.8508 1.0000 2.500 0.5721 0.00583 0.00179 -0.0717 0.7441 1.0000 3.000 0.5986 0.00716 0.00207 -0.0652 0.5074 1.0000 3.500 0.6304 0.00885 0.00266 -0.0610 0.2657 1.0000 4.000 0.6716 0.01027 0.00334 -0.0587 0.1123 1.0000 4.500 0.7165 0.01148 0.00429 -0.0570 0.0388 1.0000 5.000 0.7655 0.01220 0.00494 -0.0559 0.0222 1.0000 5.500 0.8142 0.01298 0.00569 -0.0548 0.0128 1.0000 6.000 0.8612 0.01413 0.00693 -0.0531 0.0085 1.0000 6.500 0.9076 0.01535 0.00830 -0.0514 0.0069 1.0000 7.000 0.9511 0.01718 0.01038 -0.0491 0.0060 1.0000 7.500 0.9912 0.02028 0.01390 -0.0461 0.0055 1.0000 8.000 1.0279 0.02475 0.01917 -0.0427 0.0055 1.0000 8.500 1.0396 0.03437 0.02996 -0.0357 0.0059 1.0000 9.000 1.0161 0.04739 0.04407 -0.0266 0.0065 1.0000 9.500 0.9668 0.05965 0.05678 -0.0183 0.0069 1.0000 10.000 0.9220 0.06947 0.06691 -0.0164 0.0070 1.0000 10.500 0.8800 0.08810 0.08574 -0.0301 0.0070 1.0000 11.000 0.8566 0.10425 0.10184 -0.0406 0.0070 1.0000 11.500 0.8393 0.11828 0.11584 -0.0480 0.0072 1.0000 12.000 0.8285 0.13119 0.12872 -0.0543 0.0076 1.0000 12.500 0.8210 0.14354 0.14104 -0.0601 0.0083 1.0000 14.000 0.8351 0.17309 0.17058 -0.0740 0.0118 1.0000 14.500 0.8428 0.18223 0.17971 -0.0783 0.0118 1.0000 15.000 0.8520 0.19133 0.18880 -0.0824 0.0116 1.0000 15.500 0.8621 0.20042 0.19789 -0.0864 0.0114 1.0000 16.000 0.8727 0.20962 0.20708 -0.0902 0.0111 1.0000 16.500 0.8834 0.21915 0.21661 -0.0938 0.0108 1.0000 17.000 0.8951 0.22891 0.22652 -0.0963 0.0100 1.0000 17.500 0.8968 0.24529 0.24287 -0.1007 0.0093 1.0000 18.000 0.9060 0.25577 0.25336 -0.1047 0.0093 1.0000 18.500 0.9145 0.26631 0.26391 -0.1087 0.0093 1.0000 19.000 0.9222 0.27685 0.27447 -0.1125 0.0092 1.0000 19.500 0.9287 0.28730 0.28494 -0.1162 0.0091 1.0000 20.000 0.9339 0.29733 0.29499 -0.1200 0.0090 1.0000 20.500 0.9380 0.30657 0.30426 -0.1239 0.0084 1.0000 21.000 0.9402 0.31603 0.31375 -0.1271 0.0070 1.0000 21.500 0.8817 0.31091 0.30880 -0.1235 0.0073 1.0000 22.000 0.8644 0.31156 0.30951 -0.1239 0.0055 1.0000 22.500 0.8541 0.31322 0.31122 -0.1249 0.0048 1.0000 23.000 0.8473 0.31535 0.31339 -0.1263 0.0042 1.0000 23.500 0.8424 0.31789 0.31599 -0.1279 0.0041 1.0000 24.000 0.8390 0.32036 0.31850 -0.1295 0.0036 1.0000 24.500 0.8365 0.32280 0.32101 -0.1312 0.0032 1.0000 25.000 0.8341 0.32483 0.32307 -0.1327 0.0028 1.0000 25.500 0.8327 0.32812 0.32640 -0.1347 0.0029 1.0000 27.000 0.8227 0.33867 0.33703 -0.1392 0.0024 1.0000