XFOIL Version 6.94 Calculated polar for: AH 83-159 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 0.3936 0.01341 0.00858 -0.0748 0.6886 0.8527 0.500 0.4395 0.01328 0.00846 -0.0728 0.6846 0.8600 1.000 0.4920 0.01324 0.00840 -0.0725 0.6796 0.8659 1.500 0.5493 0.01321 0.00834 -0.0737 0.6750 0.8708 2.000 0.6108 0.01323 0.00829 -0.0757 0.6702 0.8753 2.500 0.6659 0.01300 0.00801 -0.0762 0.6651 0.8785 3.000 0.7165 0.01314 0.00819 -0.0758 0.6590 0.8825 3.500 0.7705 0.01292 0.00806 -0.0762 0.6529 0.8857 4.000 0.8275 0.01275 0.00791 -0.0771 0.6457 0.8886 4.500 0.8865 0.01261 0.00780 -0.0785 0.6394 0.8916 5.000 0.9465 0.01265 0.00787 -0.0802 0.6316 0.8944 5.500 1.0028 0.01270 0.00805 -0.0813 0.6240 0.8962 6.000 1.0571 0.01242 0.00787 -0.0818 0.6137 0.8982 6.500 1.1126 0.01214 0.00761 -0.0822 0.6021 0.9004 7.000 1.1623 0.01202 0.00768 -0.0818 0.5855 0.9028 7.500 1.2087 0.01191 0.00757 -0.0805 0.5543 0.9059 8.000 1.2318 0.01261 0.00793 -0.0757 0.4772 0.9097 8.500 1.2609 0.01346 0.00880 -0.0724 0.4468 0.9123 9.000 1.2267 0.01798 0.01260 -0.0627 0.3303 0.9158 9.500 1.2031 0.02268 0.01673 -0.0556 0.2343 0.9191 10.000 1.1283 0.03135 0.02402 -0.0450 0.0511 0.9236 10.500 1.2135 0.02928 0.02302 -0.0485 0.1426 0.9250 11.000 1.2091 0.03375 0.02713 -0.0449 0.0853 0.9269 11.500 1.1936 0.03945 0.03232 -0.0409 0.0195 0.9287 12.000 1.2134 0.04258 0.03556 -0.0397 0.0134 0.9302 13.000 1.2407 0.05032 0.04365 -0.0372 0.0080 0.9327 13.500 1.2309 0.05674 0.05033 -0.0350 0.0052 0.9339 14.000 1.2246 0.06326 0.05714 -0.0335 0.0049 0.9354 14.500 1.2276 0.06888 0.06300 -0.0330 0.0049 0.9381 15.000 1.2310 0.07457 0.06892 -0.0327 0.0049 0.9400 15.500 1.2227 0.08162 0.07627 -0.0317 0.0048 0.9412 16.000 1.2289 0.08704 0.08192 -0.0318 0.0048 0.9427 16.500 1.2311 0.09329 0.08847 -0.0322 0.0050 0.9444 17.000 1.2317 0.10003 0.09552 -0.0329 0.0051 0.9463 18.500 1.1831 0.13043 0.12729 -0.0425 0.0062 0.9555 19.000 1.1376 0.14736 0.14475 -0.0518 0.0068 0.9602 20.000 1.0656 0.18438 0.18240 -0.0754 0.0070 1.0000 21.500 0.9787 0.26980 0.26789 -0.1087 0.0147 1.0000 22.000 0.9858 0.28217 0.28026 -0.1141 0.0134 1.0000 22.500 0.9937 0.29368 0.29177 -0.1190 0.0124 1.0000 23.000 1.0023 0.30442 0.30253 -0.1235 0.0117 1.0000 23.500 1.0111 0.31455 0.31267 -0.1277 0.0111 1.0000 24.000 1.0201 0.32403 0.32217 -0.1312 0.0106 1.0000 24.500 1.0262 0.33458 0.33275 -0.1346 0.0100 1.0000 26.000 1.0242 0.37701 0.37521 -0.1453 0.0095 1.0000 26.500 1.0186 0.38874 0.38697 -0.1477 0.0095 1.0000