XFOIL Version 6.94 Calculated polar for: HT22 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 0.0799 0.00454 0.00123 -0.0092 0.9940 0.9999 0.500 0.1436 0.00496 0.00112 -0.0096 0.7921 0.9999 1.000 0.1934 0.00577 0.00111 -0.0077 0.6033 0.9999 1.500 0.2476 0.00636 0.00118 -0.0072 0.4895 0.9999 2.000 0.3027 0.00682 0.00131 -0.0069 0.4129 0.9999 2.500 0.3581 0.00725 0.00147 -0.0067 0.3477 0.9999 3.000 0.4134 0.00771 0.00170 -0.0065 0.2827 0.9999 3.500 0.4685 0.00828 0.00200 -0.0063 0.2112 0.9999 4.000 0.5232 0.00902 0.00243 -0.0061 0.1400 0.9999 4.500 0.5778 0.00986 0.00305 -0.0060 0.0870 0.9999 5.000 0.6321 0.01085 0.00393 -0.0057 0.0604 0.9999 5.500 0.6863 0.01178 0.00488 -0.0053 0.0480 0.9999 6.000 0.7397 0.01294 0.00608 -0.0049 0.0408 0.9999 6.500 0.7924 0.01420 0.00743 -0.0044 0.0356 0.9999 7.000 0.8439 0.01588 0.00926 -0.0037 0.0320 0.9999 7.500 0.8947 0.01759 0.01110 -0.0031 0.0286 0.9999 8.000 0.9449 0.01935 0.01304 -0.0025 0.0259 0.9999 8.500 0.9925 0.02219 0.01634 -0.0015 0.0236 0.9999 9.000 1.0384 0.02470 0.01913 -0.0009 0.0212 0.9999 9.500 1.0818 0.02760 0.02254 -0.0001 0.0190 0.9999 10.000 1.1129 0.03320 0.02887 0.0006 0.0176 0.9999 10.500 1.1160 0.04342 0.04024 -0.0002 0.0165 0.9999 11.000 1.0678 0.06212 0.05975 -0.0161 0.0169 0.9999 11.500 1.0110 0.08779 0.08555 -0.0373 0.0179 0.9999 12.000 0.8488 0.14523 0.14282 -0.0644 0.0280 0.9999 12.500 0.8579 0.15209 0.14969 -0.0663 0.0259 0.9999 13.000 0.8631 0.16063 0.15822 -0.0685 0.0252 0.9999 13.500 0.8602 0.17295 0.17052 -0.0759 0.0229 0.9999 14.000 0.8720 0.17978 0.17737 -0.0779 0.0220 0.9999 14.500 0.8847 0.18722 0.18482 -0.0792 0.0216 0.9999 15.000 0.8869 0.19895 0.19652 -0.0875 0.0197 0.9999 15.500 0.9022 0.20454 0.20213 -0.0892 0.0184 0.9999 16.000 0.9124 0.21369 0.21127 -0.0936 0.0180 0.9999 16.500 0.9245 0.22296 0.22055 -0.0992 0.0158 0.9999