XFOIL Version 6.94 Calculated polar for: SD6080 (9.2%) 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 0.4010 0.00638 0.00192 -0.0801 0.7004 1.0000 0.500 0.4558 0.00651 0.00188 -0.0797 0.6845 1.0000 1.000 0.5108 0.00665 0.00187 -0.0794 0.6680 1.0000 1.500 0.5659 0.00681 0.00191 -0.0791 0.6512 1.0000 2.000 0.6209 0.00699 0.00198 -0.0789 0.6336 1.0000 2.500 0.6757 0.00718 0.00207 -0.0786 0.6150 1.0000 3.000 0.7306 0.00737 0.00223 -0.0783 0.5949 1.0000 3.500 0.7852 0.00758 0.00240 -0.0780 0.5730 1.0000 4.000 0.8392 0.00784 0.00261 -0.0776 0.5486 1.0000 4.500 0.8929 0.00811 0.00287 -0.0772 0.5204 1.0000 5.000 0.9456 0.00848 0.00320 -0.0767 0.4864 1.0000 5.500 0.9970 0.00897 0.00359 -0.0760 0.4445 1.0000 6.000 1.0446 0.00978 0.00415 -0.0748 0.3725 1.0000 6.500 1.0898 0.01086 0.00490 -0.0734 0.2971 1.0000 7.000 1.1321 0.01220 0.00587 -0.0718 0.2180 1.0000 7.500 1.1754 0.01340 0.00685 -0.0702 0.1629 1.0000 8.000 1.2148 0.01486 0.00803 -0.0682 0.1073 1.0000 8.500 1.2451 0.01699 0.00974 -0.0649 0.0390 1.0000 9.500 1.3019 0.02075 0.01360 -0.0574 0.0160 1.0000 10.000 1.3202 0.02264 0.01567 -0.0523 0.0147 1.0000 10.500 1.3320 0.02516 0.01839 -0.0473 0.0139 1.0000 11.000 1.3347 0.02870 0.02215 -0.0425 0.0133 1.0000 11.500 1.3317 0.03337 0.02706 -0.0384 0.0127 1.0000 12.000 1.3406 0.03743 0.03136 -0.0358 0.0126 1.0000 12.500 1.3503 0.04165 0.03583 -0.0339 0.0122 1.0000 13.000 1.3570 0.04651 0.04098 -0.0324 0.0118 1.0000 13.500 1.3595 0.05223 0.04701 -0.0312 0.0116 1.0000 14.000 1.3576 0.05877 0.05389 -0.0309 0.0114 1.0000 14.500 1.3489 0.06663 0.06212 -0.0315 0.0113 1.0000 15.000 1.3319 0.07627 0.07215 -0.0338 0.0114 1.0000 15.500 1.3080 0.08779 0.08406 -0.0381 0.0114 1.0000 16.000 1.2785 0.10145 0.09812 -0.0447 0.0114 1.0000 16.500 1.2434 0.11760 0.11464 -0.0537 0.0116 1.0000 17.000 1.2056 0.13616 0.13354 -0.0652 0.0117 1.0000 17.500 1.1634 0.15794 0.15562 -0.0792 0.0121 1.0000 18.000 1.0845 0.19845 0.19639 -0.1026 0.0137 1.0000 20.000 0.8382 0.24314 0.24142 -0.1189 0.0198 1.0000 21.000 0.8547 0.26050 0.25883 -0.1254 0.0173 1.0000 21.500 0.8594 0.27106 0.26939 -0.1302 0.0149 1.0000 22.000 0.8696 0.27819 0.27655 -0.1330 0.0134 1.0000 22.500 0.8795 0.28795 0.28632 -0.1355 0.0127 1.0000 23.000 0.8816 0.29925 0.29763 -0.1407 0.0121 1.0000 24.000 0.8983 0.31625 0.31469 -0.1470 0.0091 1.0000 24.500 0.9055 0.32716 0.32561 -0.1500 0.0088 1.0000 25.000 0.9094 0.33956 0.33800 -0.1548 0.0076 1.0000 25.500 0.9161 0.34957 0.34803 -0.1581 0.0072 1.0000 26.000 0.9225 0.35893 0.35741 -0.1614 0.0064 1.0000 26.500 0.9293 0.36744 0.36596 -0.1644 0.0060 1.0000 27.000 0.9362 0.37815 0.37669 -0.1671 0.0057 1.0000