XFOIL Version 6.94 Calculated polar for: HQ 2.5/9 B 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 0.3706 0.00667 0.00225 -0.0832 0.8126 0.7871 0.500 0.4252 0.00665 0.00222 -0.0826 0.7986 0.8118 1.000 0.4788 0.00662 0.00226 -0.0818 0.7836 0.8379 1.500 0.5310 0.00658 0.00228 -0.0807 0.7666 0.8697 2.000 0.5809 0.00648 0.00226 -0.0789 0.7458 0.9133 2.500 0.6438 0.00639 0.00221 -0.0800 0.7136 1.0000 3.000 0.6952 0.00665 0.00220 -0.0789 0.6324 1.0000 3.500 0.7378 0.00770 0.00252 -0.0765 0.4796 1.0000 4.000 0.7807 0.00897 0.00307 -0.0745 0.3498 1.0000 5.500 0.9149 0.01263 0.00512 -0.0701 0.0621 1.0000 6.000 0.9631 0.01347 0.00586 -0.0690 0.0386 1.0000 6.500 1.0089 0.01453 0.00679 -0.0676 0.0176 1.0000 7.000 1.0561 0.01538 0.00765 -0.0663 0.0129 1.0000 7.500 1.1030 0.01619 0.00854 -0.0650 0.0105 1.0000 8.000 1.1464 0.01730 0.00966 -0.0632 0.0027 1.0000 8.500 1.1890 0.01842 0.01091 -0.0612 0.0021 1.0000 9.000 1.2293 0.01965 0.01232 -0.0589 0.0020 1.0000 9.500 1.2663 0.02105 0.01392 -0.0561 0.0020 1.0000 10.000 1.2990 0.02263 0.01574 -0.0528 0.0020 1.0000 10.500 1.3234 0.02435 0.01771 -0.0481 0.0020 1.0000 11.000 1.3425 0.02637 0.02001 -0.0431 0.0020 1.0000 11.500 1.3564 0.02884 0.02277 -0.0381 0.0020 1.0000 12.000 1.3646 0.03186 0.02610 -0.0333 0.0020 1.0000 12.500 1.3651 0.03573 0.03031 -0.0289 0.0021 1.0000 13.000 1.3588 0.04064 0.03556 -0.0256 0.0021 1.0000 13.500 1.3448 0.04699 0.04227 -0.0237 0.0021 1.0000 14.000 1.3250 0.05505 0.05068 -0.0241 0.0021 1.0000 14.500 1.2981 0.06576 0.06175 -0.0278 0.0021 1.0000 15.000 1.2654 0.08005 0.07641 -0.0354 0.0022 1.0000 15.500 1.2300 0.09695 0.09366 -0.0454 0.0022 1.0000 16.000 1.1907 0.11586 0.11286 -0.0566 0.0022 1.0000 16.500 1.1514 0.13610 0.13336 -0.0685 0.0022 1.0000 17.000 1.1138 0.15718 0.15464 -0.0808 0.0022 1.0000 17.500 1.0839 0.17708 0.17470 -0.0922 0.0022 1.0000 18.000 1.0648 0.19480 0.19251 -0.1022 0.0022 1.0000 18.500 1.0520 0.21143 0.20921 -0.1112 0.0023 1.0000 19.000 1.0174 0.24597 0.24366 -0.1244 0.0057 1.0000