XFOIL Version 6.94 Calculated polar for: SD7080 (9.2%) 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 0.3479 0.00699 0.00272 -0.0728 0.8538 1.0000 0.500 0.3926 0.00691 0.00243 -0.0701 0.8189 1.0000 1.000 0.4400 0.00696 0.00227 -0.0678 0.7764 1.0000 1.500 0.4892 0.00715 0.00219 -0.0660 0.7282 1.0000 2.000 0.5389 0.00747 0.00224 -0.0643 0.6768 1.0000 2.500 0.5887 0.00787 0.00237 -0.0629 0.6239 1.0000 3.000 0.6386 0.00833 0.00259 -0.0615 0.5705 1.0000 3.500 0.6885 0.00882 0.00287 -0.0603 0.5175 1.0000 4.000 0.7383 0.00937 0.00321 -0.0590 0.4655 1.0000 4.500 0.7879 0.00996 0.00365 -0.0579 0.4156 1.0000 5.000 0.8372 0.01061 0.00413 -0.0567 0.3681 1.0000 5.500 0.8859 0.01132 0.00471 -0.0556 0.3239 1.0000 6.000 0.9345 0.01206 0.00535 -0.0544 0.2801 1.0000 6.500 0.9820 0.01288 0.00606 -0.0531 0.2358 1.0000 7.000 1.0284 0.01381 0.00691 -0.0518 0.1970 1.0000 7.500 1.0739 0.01480 0.00779 -0.0503 0.1536 1.0000 8.000 1.1176 0.01596 0.00884 -0.0487 0.1184 1.0000 8.500 1.1600 0.01720 0.01005 -0.0469 0.0868 1.0000 9.000 1.1998 0.01863 0.01142 -0.0448 0.0551 1.0000 9.500 1.2255 0.02139 0.01403 -0.0407 0.0215 1.0000 10.500 1.2604 0.02654 0.01968 -0.0301 0.0153 1.0000 11.000 1.2697 0.02942 0.02278 -0.0247 0.0142 1.0000 11.500 1.2740 0.03303 0.02661 -0.0200 0.0136 1.0000 12.000 1.2729 0.03773 0.03159 -0.0160 0.0131 1.0000 12.500 1.2637 0.04437 0.03859 -0.0131 0.0125 1.0000 13.000 1.2624 0.04975 0.04433 -0.0122 0.0121 1.0000 13.500 1.2517 0.05716 0.05214 -0.0127 0.0120 1.0000 14.000 1.2344 0.06623 0.06163 -0.0154 0.0119 1.0000 14.500 1.2104 0.07740 0.07319 -0.0204 0.0117 1.0000 15.000 1.1799 0.09103 0.08719 -0.0277 0.0119 1.0000 15.500 1.1460 0.10683 0.10334 -0.0372 0.0119 1.0000 16.000 1.1077 0.12521 0.12201 -0.0486 0.0122 1.0000 16.500 1.0661 0.14636 0.14342 -0.0618 0.0124 1.0000