XFOIL Version 6.94 Calculated polar for: 74-130 WP2 MOD 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 0.3557 0.01353 0.00850 -0.0750 0.7574 0.9374 0.500 0.4134 0.01330 0.00811 -0.0755 0.7522 0.9450 1.000 0.4624 0.01330 0.00809 -0.0750 0.7435 0.9508 1.500 0.5168 0.01314 0.00792 -0.0755 0.7344 0.9555 2.000 0.5751 0.01288 0.00760 -0.0765 0.7281 0.9594 2.500 0.6364 0.01268 0.00734 -0.0781 0.7228 0.9626 3.000 0.6888 0.01283 0.00758 -0.0786 0.7131 0.9662 3.500 0.7456 0.01274 0.00760 -0.0796 0.7041 0.9703 4.000 0.8073 0.01253 0.00743 -0.0814 0.6977 0.9739 4.500 0.8730 0.01239 0.00733 -0.0839 0.6904 0.9763 5.000 0.9302 0.01201 0.00719 -0.0848 0.6750 0.9808 5.500 0.9949 0.01125 0.00648 -0.0865 0.6539 0.9842 6.000 1.0547 0.01094 0.00619 -0.0876 0.6209 0.9897 6.500 1.1120 0.01113 0.00644 -0.0887 0.5904 1.0000 7.000 1.1503 0.01157 0.00699 -0.0862 0.5500 1.0000 7.500 1.1753 0.01278 0.00785 -0.0819 0.4429 1.0000 8.000 1.1411 0.01748 0.01133 -0.0713 0.2488 1.0000 8.500 1.1218 0.02276 0.01558 -0.0648 0.0926 1.0000 9.000 1.1325 0.02611 0.01862 -0.0614 0.0437 1.0000 9.500 1.1404 0.02985 0.02224 -0.0575 0.0159 1.0000 10.000 1.1394 0.03443 0.02704 -0.0526 0.0091 1.0000 10.500 1.1495 0.03828 0.03118 -0.0492 0.0084 1.0000 11.000 1.1644 0.04194 0.03509 -0.0460 0.0087 1.0000 11.500 1.1880 0.04575 0.03922 -0.0423 0.0079 1.0000 12.000 1.2192 0.05064 0.04463 -0.0390 0.0082 1.0000 12.500 1.2276 0.05781 0.05242 -0.0357 0.0086 1.0000 13.000 1.2084 0.06708 0.06231 -0.0325 0.0090 1.0000