XFOIL Version 6.94 Calculated polar for: HQ 2.0/12 AIRFOIL 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 0.2740 0.00752 0.00248 -0.0589 0.7405 0.7264 0.500 0.3290 0.00756 0.00248 -0.0584 0.7236 0.7456 1.000 0.3843 0.00757 0.00247 -0.0580 0.7064 0.7594 1.500 0.4393 0.00757 0.00247 -0.0576 0.6878 0.7737 2.000 0.4942 0.00761 0.00254 -0.0572 0.6687 0.7894 2.500 0.5482 0.00768 0.00261 -0.0567 0.6462 0.8065 3.000 0.6011 0.00774 0.00270 -0.0559 0.6209 0.8251 3.500 0.6529 0.00781 0.00282 -0.0549 0.5876 0.8467 4.000 0.7009 0.00796 0.00296 -0.0531 0.5390 0.8744 4.500 0.7441 0.00850 0.00324 -0.0505 0.4385 0.9300 5.000 0.8014 0.00984 0.00388 -0.0521 0.3031 1.0000 5.500 0.8455 0.01072 0.00445 -0.0505 0.2481 1.0000 6.000 0.8912 0.01146 0.00499 -0.0490 0.2062 1.0000 6.500 0.9372 0.01214 0.00554 -0.0476 0.1724 1.0000 7.000 0.9748 0.01337 0.00636 -0.0450 0.1065 1.0000 7.500 1.0116 0.01458 0.00732 -0.0422 0.0658 1.0000 8.000 1.0492 0.01563 0.00827 -0.0394 0.0450 1.0000 8.500 1.0841 0.01674 0.00929 -0.0363 0.0287 1.0000 9.000 1.1124 0.01788 0.01038 -0.0320 0.0151 1.0000 9.500 1.1319 0.01947 0.01197 -0.0266 0.0037 1.0000 10.000 1.1577 0.02080 0.01343 -0.0225 0.0033 1.0000 10.500 1.1811 0.02234 0.01514 -0.0184 0.0030 1.0000 11.000 1.2026 0.02412 0.01709 -0.0146 0.0029 1.0000 11.500 1.2204 0.02626 0.01944 -0.0109 0.0028 1.0000 12.000 1.2360 0.02874 0.02212 -0.0076 0.0028 1.0000 12.500 1.2473 0.03172 0.02533 -0.0045 0.0027 1.0000 13.000 1.2547 0.03527 0.02912 -0.0020 0.0027 1.0000 13.500 1.2566 0.03963 0.03372 0.0000 0.0027 1.0000 14.000 1.2530 0.04496 0.03931 0.0010 0.0027 1.0000 14.500 1.2458 0.05125 0.04586 0.0008 0.0027 1.0000 15.000 1.2329 0.05901 0.05388 -0.0008 0.0027 1.0000 15.500 1.2139 0.06864 0.06380 -0.0041 0.0027 1.0000 16.000 1.1915 0.07994 0.07539 -0.0092 0.0027 1.0000 16.500 1.1674 0.09258 0.08831 -0.0155 0.0027 1.0000 17.000 1.1396 0.10677 0.10277 -0.0231 0.0028 1.0000 17.500 1.1141 0.12099 0.11724 -0.0309 0.0028 1.0000 18.000 1.0916 0.13495 0.13142 -0.0388 0.0029 1.0000 18.500 1.0727 0.14849 0.14515 -0.0466 0.0029 1.0000 19.000 1.0593 0.16104 0.15787 -0.0540 0.0030 1.0000 19.500 1.0486 0.17319 0.17018 -0.0612 0.0030 1.0000 20.000 1.0396 0.18521 0.18235 -0.0684 0.0031 1.0000 20.500 1.0286 0.19813 0.19543 -0.0761 0.0032 1.0000 21.000 1.0141 0.21291 0.21038 -0.0845 0.0033 1.0000