XFOIL Version 6.94 Calculated polar for: AQUILA 9.3% smoothed 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 0.3933 0.01080 0.00309 -0.0665 0.6682 0.0636 0.500 0.4861 0.00810 0.00269 -0.0743 0.6461 1.0000 1.000 0.5356 0.00828 0.00263 -0.0728 0.6240 1.0000 1.500 0.5852 0.00850 0.00262 -0.0714 0.6024 1.0000 2.000 0.6350 0.00876 0.00267 -0.0700 0.5813 1.0000 2.500 0.6849 0.00900 0.00280 -0.0687 0.5589 1.0000 3.000 0.7349 0.00928 0.00295 -0.0674 0.5365 1.0000 3.500 0.7847 0.00962 0.00316 -0.0662 0.5142 1.0000 4.000 0.8347 0.00993 0.00342 -0.0650 0.4901 1.0000 4.500 0.8842 0.01032 0.00373 -0.0638 0.4663 1.0000 5.000 0.9335 0.01073 0.00410 -0.0626 0.4417 1.0000 5.500 0.9821 0.01120 0.00453 -0.0614 0.4166 1.0000 6.000 1.0305 0.01171 0.00503 -0.0601 0.3917 1.0000 6.500 1.0779 0.01229 0.00560 -0.0587 0.3673 1.0000 7.000 1.1248 0.01291 0.00624 -0.0573 0.3435 1.0000 7.500 1.1698 0.01360 0.00693 -0.0557 0.3175 1.0000 8.000 1.2137 0.01429 0.00766 -0.0540 0.2886 1.0000 8.500 1.2560 0.01512 0.00852 -0.0520 0.2646 1.0000 9.000 1.2954 0.01602 0.00945 -0.0497 0.2340 1.0000 9.500 1.3322 0.01705 0.01050 -0.0471 0.2019 1.0000 10.000 1.3615 0.01845 0.01182 -0.0436 0.1565 1.0000 10.500 1.3762 0.02041 0.01358 -0.0380 0.1073 1.0000 11.500 1.3773 0.02636 0.01929 -0.0260 0.0441 1.0000 12.000 1.3662 0.03106 0.02404 -0.0215 0.0268 1.0000 12.500 1.3570 0.03641 0.02961 -0.0188 0.0209 1.0000 13.000 1.3402 0.04327 0.03667 -0.0177 0.0177 1.0000 13.500 1.3304 0.04999 0.04366 -0.0177 0.0165 1.0000 14.000 1.3196 0.05728 0.05121 -0.0184 0.0155 1.0000 14.500 1.3088 0.06502 0.05919 -0.0197 0.0147 1.0000 15.000 1.2985 0.07315 0.06752 -0.0216 0.0139 1.0000 15.500 1.2877 0.08161 0.07617 -0.0238 0.0132 1.0000 16.000 1.2798 0.08980 0.08456 -0.0259 0.0128 1.0000 16.500 1.2723 0.09801 0.09302 -0.0277 0.0125 1.0000 17.000 1.2582 0.10793 0.10327 -0.0306 0.0122 1.0000 17.500 1.2434 0.11883 0.11450 -0.0355 0.0121 1.0000 18.000 1.2242 0.13125 0.12728 -0.0420 0.0121 1.0000 18.500 1.1998 0.14537 0.14171 -0.0500 0.0122 1.0000 19.000 1.1777 0.15998 0.15663 -0.0590 0.0122 1.0000 19.500 1.1573 0.17531 0.17221 -0.0688 0.0124 1.0000 20.000 1.0441 0.23077 0.22793 -0.0978 0.0169 1.0000 20.500 0.8093 0.23656 0.23429 -0.1000 0.0313 1.0000 21.000 0.8147 0.24580 0.24355 -0.1042 0.0285 1.0000 21.500 0.8237 0.25349 0.25127 -0.1074 0.0264 1.0000