XFOIL Version 6.94 Calculated polar for: AH 94-145 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 0.6487 0.01049 0.00550 -0.1340 0.6506 0.8658 0.500 0.6976 0.01062 0.00566 -0.1323 0.6467 0.9064 1.000 0.7353 0.01058 0.00562 -0.1278 0.6428 0.9494 1.500 0.7904 0.01048 0.00545 -0.1273 0.6394 0.9998 2.000 0.8517 0.01087 0.00579 -0.1292 0.6354 0.9998 2.500 0.9126 0.01108 0.00603 -0.1309 0.6311 0.9998 3.000 0.9737 0.01128 0.00623 -0.1326 0.6265 0.9998 3.500 1.0352 0.01143 0.00636 -0.1342 0.6224 0.9998 4.000 1.0967 0.01165 0.00653 -0.1358 0.6182 0.9998 4.500 1.1547 0.01195 0.00691 -0.1369 0.6128 0.9998 5.000 1.2136 0.01193 0.00696 -0.1379 0.6057 0.9998 5.500 1.2744 0.01177 0.00671 -0.1390 0.5971 0.9998 6.000 1.3302 0.01161 0.00668 -0.1393 0.5859 0.9998 6.500 1.3869 0.01155 0.00665 -0.1398 0.5751 0.9998 7.000 1.4417 0.01162 0.00682 -0.1401 0.5635 0.9998 7.500 1.4945 0.01177 0.00708 -0.1400 0.5483 0.9998 8.000 1.5444 0.01201 0.00738 -0.1394 0.5267 0.9998 8.500 1.5897 0.01251 0.00790 -0.1382 0.4993 0.9998 9.000 1.6197 0.01365 0.00891 -0.1345 0.4481 0.9998 9.500 1.6126 0.01641 0.01133 -0.1258 0.3763 0.9998 10.000 1.5881 0.02165 0.01624 -0.1181 0.3079 0.9998 10.500 1.5669 0.02769 0.02202 -0.1125 0.2518 0.9998 11.000 1.5526 0.03332 0.02746 -0.1078 0.2061 0.9998 11.500 1.5429 0.03861 0.03260 -0.1036 0.1691 0.9998 12.000 1.5378 0.04377 0.03765 -0.1001 0.1389 0.9998 12.500 1.5383 0.04866 0.04246 -0.0973 0.1138 0.9998 13.000 1.5397 0.05361 0.04736 -0.0948 0.0946 0.9998 13.500 1.5440 0.05846 0.05221 -0.0927 0.0798 0.9998 14.000 1.5503 0.06321 0.05701 -0.0909 0.0685 0.9998 14.500 1.5539 0.06833 0.06221 -0.0892 0.0597 0.9998 15.000 1.5574 0.07362 0.06755 -0.0878 0.0526 0.9998 15.500 1.5599 0.07916 0.07322 -0.0865 0.0471 0.9998 16.000 1.5654 0.08437 0.07854 -0.0856 0.0426 0.9998 16.500 1.5549 0.09163 0.08590 -0.0847 0.0379 0.9998 17.000 1.5638 0.09669 0.09117 -0.0844 0.0357 0.9998 17.500 1.5668 0.10254 0.09718 -0.0844 0.0329 0.9998 18.000 1.5612 0.10957 0.10432 -0.0847 0.0302 0.9998 18.500 1.5544 0.11674 0.11166 -0.0852 0.0279 0.9998 19.000 1.5578 0.12285 0.11797 -0.0862 0.0262 0.9998 19.500 1.5572 0.12961 0.12491 -0.0878 0.0244 0.9998 20.000 1.5526 0.13701 0.13245 -0.0899 0.0229 0.9998 20.500 1.5411 0.14523 0.14081 -0.0924 0.0210 0.9998 21.000 1.5388 0.15258 0.14841 -0.0953 0.0201 0.9998 21.500 1.5359 0.16031 0.15637 -0.0989 0.0191 0.9998 22.000 1.5317 0.16841 0.16467 -0.1032 0.0180 0.9998 22.500 1.5265 0.17681 0.17324 -0.1081 0.0171 0.9998 23.000 1.5196 0.18568 0.18225 -0.1137 0.0161 0.9998 23.500 1.5060 0.19553 0.19228 -0.1200 0.0149 0.9998 24.000 1.4952 0.20604 0.20306 -0.1274 0.0145 0.9998 24.500 1.4828 0.21745 0.21474 -0.1358 0.0141 0.9998 25.000 1.4652 0.23079 0.22836 -0.1459 0.0137 0.9998 25.500 1.4341 0.24927 0.24717 -0.1599 0.0133 0.9998