XFOIL Version 6.94 Calculated polar for: 74-130 WP2 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 0.4041 0.01382 0.00940 -0.0900 0.7395 0.8930 0.500 0.4552 0.01390 0.00943 -0.0896 0.7358 0.9007 1.000 0.5079 0.01405 0.00957 -0.0896 0.7328 0.9057 1.500 0.5652 0.01403 0.00951 -0.0905 0.7295 0.9095 2.000 0.6240 0.01406 0.00951 -0.0918 0.7266 0.9123 2.500 0.6824 0.01434 0.00978 -0.0931 0.7237 0.9150 3.000 0.7359 0.01474 0.01023 -0.0937 0.7189 0.9171 3.500 0.7900 0.01459 0.01022 -0.0942 0.7129 0.9197 4.000 0.8477 0.01417 0.00987 -0.0949 0.7063 0.9228 4.500 0.9123 0.01324 0.00898 -0.0964 0.6999 0.9246 5.000 0.9800 0.01227 0.00806 -0.0983 0.6911 0.9262 5.500 1.0399 0.01087 0.00682 -0.0988 0.6735 0.9287 6.000 1.1000 0.01012 0.00616 -0.0997 0.6553 0.9310 6.500 1.1530 0.00972 0.00584 -0.0994 0.6106 0.9339 7.000 1.1313 0.01229 0.00717 -0.0862 0.3855 0.9452 8.000 1.0950 0.02060 0.01388 -0.0704 0.1021 1.0000 8.500 1.1118 0.02364 0.01651 -0.0677 0.0403 1.0000 9.000 1.1416 0.02569 0.01863 -0.0662 0.0288 1.0000 9.500 1.1587 0.02874 0.02161 -0.0632 0.0090 1.0000 10.000 1.1776 0.03165 0.02472 -0.0603 0.0060 1.0000 10.500 1.1836 0.03563 0.02900 -0.0561 0.0053 1.0000 11.000 1.1944 0.03949 0.03311 -0.0524 0.0051 1.0000 11.500 1.2113 0.04303 0.03691 -0.0492 0.0052 1.0000 12.000 1.2322 0.04666 0.04088 -0.0459 0.0054 1.0000 12.500 1.2581 0.05398 0.04904 -0.0409 0.0066 1.0000 13.000 1.2357 0.06479 0.06062 -0.0361 0.0080 1.0000 13.500 1.1970 0.07523 0.07158 -0.0334 0.0086 1.0000