XFOIL Version 6.94 Calculated polar for: S7075 (9%) 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 0.3936 0.00625 0.00252 -0.0894 0.8577 0.9147 0.500 0.4606 0.00599 0.00225 -0.0909 0.8391 0.9734 1.000 0.5244 0.00592 0.00205 -0.0924 0.8144 1.0000 1.500 0.5771 0.00596 0.00195 -0.0914 0.7789 1.0000 2.000 0.6295 0.00614 0.00191 -0.0904 0.7336 1.0000 2.500 0.6806 0.00649 0.00200 -0.0891 0.6796 1.0000 3.000 0.7302 0.00696 0.00220 -0.0877 0.6204 1.0000 3.500 0.7794 0.00748 0.00247 -0.0863 0.5609 1.0000 4.000 0.8274 0.00809 0.00282 -0.0848 0.4960 1.0000 4.500 0.8746 0.00879 0.00323 -0.0832 0.4271 1.0000 5.000 0.9210 0.00959 0.00372 -0.0816 0.3550 1.0000 5.500 0.9666 0.01051 0.00433 -0.0800 0.2830 1.0000 6.000 1.0119 0.01150 0.00501 -0.0783 0.2160 1.0000 6.500 1.0562 0.01256 0.00581 -0.0766 0.1572 1.0000 7.000 1.0995 0.01373 0.00673 -0.0747 0.1071 1.0000 7.500 1.1407 0.01504 0.00785 -0.0725 0.0686 1.0000 8.000 1.1801 0.01646 0.00924 -0.0699 0.0501 1.0000 8.500 1.2183 0.01785 0.01069 -0.0671 0.0419 1.0000 9.000 1.2509 0.01957 0.01261 -0.0635 0.0380 1.0000 9.500 1.2841 0.02098 0.01419 -0.0599 0.0351 1.0000 10.000 1.3121 0.02253 0.01586 -0.0557 0.0324 1.0000 10.500 1.3253 0.02576 0.01928 -0.0500 0.0291 1.0000 11.000 1.3574 0.02664 0.02034 -0.0470 0.0273 1.0000 11.500 1.3807 0.02865 0.02256 -0.0432 0.0256 1.0000 12.000 1.4005 0.03098 0.02508 -0.0395 0.0242 1.0000 12.500 1.4164 0.03351 0.02776 -0.0361 0.0225 1.0000 13.000 1.4151 0.03858 0.03314 -0.0320 0.0207 1.0000 13.500 1.4322 0.04102 0.03584 -0.0299 0.0197 1.0000 14.000 1.4429 0.04454 0.03962 -0.0282 0.0181 1.0000 14.500 1.4532 0.04834 0.04357 -0.0276 0.0164 1.0000 15.000 1.4405 0.05561 0.05105 -0.0280 0.0145 1.0000 15.500 1.4591 0.05956 0.05521 -0.0293 0.0116 1.0000 16.000 1.4396 0.06959 0.06542 -0.0329 0.0102 1.0000 16.500 1.4201 0.08068 0.07686 -0.0378 0.0094 1.0000 17.000 1.3905 0.09456 0.09108 -0.0448 0.0089 1.0000 17.500 1.3578 0.11003 0.10686 -0.0533 0.0087 1.0000 18.000 1.3205 0.12739 0.12453 -0.0633 0.0085 1.0000 18.500 1.2793 0.14654 0.14398 -0.0748 0.0087 1.0000 19.000 1.2328 0.16834 0.16607 -0.0884 0.0091 1.0000