XFOIL Version 6.94 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler 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 0.3708 0.00668 0.00220 -0.0832 0.8137 0.7874 0.500 0.4250 0.00665 0.00220 -0.0825 0.7996 0.8120 1.000 0.4787 0.00662 0.00222 -0.0817 0.7846 0.8384 1.500 0.5310 0.00658 0.00224 -0.0805 0.7671 0.8703 2.000 0.5809 0.00648 0.00223 -0.0787 0.7465 0.9141 2.500 0.6443 0.00641 0.00217 -0.0800 0.7145 1.0000 3.000 0.6951 0.00669 0.00216 -0.0788 0.6234 1.0000 3.500 0.7384 0.00775 0.00249 -0.0764 0.4757 1.0000 4.000 0.7873 0.00856 0.00299 -0.0754 0.4044 1.0000 4.500 0.8369 0.00930 0.00347 -0.0744 0.3443 1.0000 5.000 0.8867 0.01000 0.00398 -0.0735 0.2884 1.0000 5.500 0.9346 0.01089 0.00457 -0.0724 0.2155 1.0000 6.000 0.9779 0.01231 0.00549 -0.0707 0.1208 1.0000 6.500 1.0234 0.01352 0.00650 -0.0692 0.0782 1.0000 7.000 1.0673 0.01489 0.00775 -0.0674 0.0485 1.0000 7.500 1.1099 0.01634 0.00926 -0.0653 0.0366 1.0000 8.000 1.1528 0.01763 0.01071 -0.0633 0.0325 1.0000 8.500 1.1933 0.01905 0.01222 -0.0610 0.0282 1.0000 9.500 1.2627 0.02290 0.01647 -0.0550 0.0222 1.0000 10.000 1.2893 0.02538 0.01909 -0.0512 0.0193 1.0000 10.500 1.3099 0.02855 0.02259 -0.0465 0.0175 1.0000 11.000 1.3305 0.03065 0.02495 -0.0421 0.0156 1.0000 11.500 1.3452 0.03303 0.02746 -0.0378 0.0141 1.0000 12.000 1.3360 0.03960 0.03449 -0.0326 0.0129 1.0000 12.500 1.3375 0.04367 0.03894 -0.0291 0.0124 1.0000 13.000 1.3282 0.04954 0.04522 -0.0267 0.0118 1.0000 13.500 1.3102 0.05709 0.05317 -0.0262 0.0114 1.0000 14.000 1.2814 0.06728 0.06378 -0.0285 0.0112 1.0000 14.500 1.2442 0.08082 0.07773 -0.0349 0.0111 1.0000 15.000 1.1964 0.09960 0.09692 -0.0466 0.0113 1.0000 15.500 1.1390 0.12369 0.12136 -0.0622 0.0118 1.0000