XFOIL Version 6.94 Calculated polar for: HQ 2.1/9.5 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3012 0.00829 0.00349 -0.0681 0.8410 0.8277 0.500 0.3533 0.00825 0.00347 -0.0669 0.8263 0.8520 1.000 0.4047 0.00816 0.00342 -0.0654 0.8116 0.8776 1.500 0.4551 0.00801 0.00331 -0.0635 0.7951 0.9087 2.000 0.5123 0.00782 0.00319 -0.0632 0.7747 0.9518 2.500 0.5848 0.00774 0.00312 -0.0666 0.7477 1.0000 3.000 0.6371 0.00778 0.00304 -0.0656 0.7001 1.0000 3.500 0.6871 0.00800 0.00302 -0.0641 0.6164 1.0000 4.000 0.7305 0.00893 0.00329 -0.0617 0.4875 1.0000 4.500 0.7763 0.00990 0.00388 -0.0600 0.4062 1.0000 5.000 0.8209 0.01095 0.00446 -0.0584 0.3095 1.0000 5.500 0.8636 0.01224 0.00515 -0.0566 0.1921 1.0000 6.000 0.9061 0.01368 0.00611 -0.0549 0.1091 1.0000 6.500 0.9492 0.01504 0.00712 -0.0533 0.0592 1.0000 7.000 0.9943 0.01614 0.00814 -0.0518 0.0377 1.0000 7.500 1.0385 0.01728 0.00930 -0.0501 0.0279 1.0000 8.000 1.0815 0.01842 0.01050 -0.0484 0.0225 1.0000 8.500 1.1229 0.01962 0.01176 -0.0465 0.0184 1.0000 9.000 1.1636 0.02078 0.01307 -0.0444 0.0163 1.0000 9.500 1.2010 0.02209 0.01454 -0.0419 0.0149 1.0000 10.000 1.2370 0.02335 0.01595 -0.0393 0.0122 1.0000 10.500 1.2673 0.02464 0.01748 -0.0357 0.0104 1.0000 11.000 1.2931 0.02615 0.01922 -0.0317 0.0073 1.0000 11.500 1.3114 0.02832 0.02147 -0.0273 0.0037 1.0000 12.000 1.3245 0.03100 0.02440 -0.0230 0.0033 1.0000 12.500 1.3339 0.03415 0.02786 -0.0192 0.0031 1.0000 13.000 1.3375 0.03805 0.03211 -0.0159 0.0030 1.0000 13.500 1.3359 0.04280 0.03721 -0.0136 0.0029 1.0000 14.000 1.3276 0.04879 0.04357 -0.0126 0.0029 1.0000 14.500 1.3119 0.05646 0.05162 -0.0134 0.0028 1.0000 15.000 1.2879 0.06667 0.06223 -0.0172 0.0028 1.0000 15.500 1.2560 0.08034 0.07629 -0.0245 0.0029 1.0000 16.000 1.2137 0.09816 0.09449 -0.0352 0.0029 1.0000 16.500 1.1593 0.12041 0.11709 -0.0487 0.0030 1.0000 17.000 1.0804 0.15152 0.14852 -0.0669 0.0033 1.0000 17.500 1.0309 0.17660 0.17382 -0.0811 0.0038 1.0000 18.000 0.9657 0.21288 0.21011 -0.0989 0.0046 1.0000 18.500 0.9686 0.22554 0.22271 -0.1050 0.0049 1.0000 19.000 0.9786 0.23472 0.23186 -0.1099 0.0051 1.0000