XFOIL Version 6.94 Calculated polar for: HQ 3.0/11 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 0.4008 0.00882 0.00370 -0.0875 0.7987 0.7889 0.500 0.4528 0.00871 0.00363 -0.0862 0.7811 0.8168 1.000 0.5046 0.00866 0.00360 -0.0849 0.7651 0.8547 1.500 0.5535 0.00847 0.00348 -0.0829 0.7485 0.9023 2.000 0.6241 0.00827 0.00330 -0.0855 0.7272 0.9772 2.500 0.6834 0.00835 0.00330 -0.0864 0.7039 1.0000 3.000 0.7367 0.00850 0.00337 -0.0860 0.6785 1.0000 3.500 0.7893 0.00869 0.00348 -0.0852 0.6488 1.0000 4.000 0.8401 0.00894 0.00366 -0.0842 0.6116 1.0000 4.500 0.8858 0.00938 0.00384 -0.0821 0.5445 1.0000 5.000 0.9236 0.01035 0.00426 -0.0788 0.4414 1.0000 5.500 0.9566 0.01172 0.00500 -0.0751 0.3279 1.0000 6.000 0.9972 0.01271 0.00574 -0.0727 0.2721 1.0000 6.500 1.0338 0.01393 0.00660 -0.0699 0.2043 1.0000 7.000 1.0721 0.01500 0.00747 -0.0673 0.1576 1.0000 7.500 1.1051 0.01635 0.00852 -0.0640 0.1045 1.0000 8.000 1.1336 0.01777 0.00971 -0.0598 0.0631 1.0000 8.500 1.1549 0.01947 0.01120 -0.0547 0.0282 1.0000 9.000 1.1723 0.02151 0.01314 -0.0493 0.0051 1.0000 9.500 1.1977 0.02311 0.01492 -0.0452 0.0044 1.0000 10.000 1.2204 0.02495 0.01699 -0.0412 0.0041 1.0000 10.500 1.2392 0.02718 0.01947 -0.0372 0.0039 1.0000 11.000 1.2541 0.02983 0.02238 -0.0333 0.0038 1.0000 11.500 1.2637 0.03305 0.02589 -0.0296 0.0038 1.0000 12.000 1.2667 0.03705 0.03017 -0.0263 0.0038 1.0000 12.500 1.2660 0.04174 0.03512 -0.0238 0.0038 1.0000 13.000 1.2603 0.04742 0.04108 -0.0223 0.0038 1.0000 13.500 1.2523 0.05398 0.04791 -0.0220 0.0038 1.0000 14.000 1.2435 0.06140 0.05560 -0.0229 0.0039 1.0000 14.500 1.2327 0.06986 0.06435 -0.0250 0.0039 1.0000 15.000 1.2210 0.07926 0.07406 -0.0282 0.0040 1.0000 15.500 1.2077 0.08968 0.08480 -0.0324 0.0041 1.0000 16.000 1.1930 0.10103 0.09647 -0.0378 0.0041 1.0000 16.500 1.1767 0.11334 0.10910 -0.0441 0.0042 1.0000 17.000 1.1579 0.12682 0.12291 -0.0516 0.0043 1.0000 17.500 1.1375 0.14130 0.13771 -0.0602 0.0045 1.0000 18.000 1.1164 0.15660 0.15331 -0.0697 0.0046 1.0000 18.500 1.0940 0.17311 0.17009 -0.0800 0.0047 1.0000 19.000 1.0680 0.19190 0.18910 -0.0914 0.0048 1.0000 19.500 1.0355 0.21526 0.21257 -0.1040 0.0052 1.0000