XFOIL Version 6.94 Calculated polar for: SIKORSKY SC1094 R8 AIRFOIL 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 0.2014 0.01037 0.00300 -0.0248 0.7444 0.0451 1.500 0.3667 0.00893 0.00283 -0.0219 0.4096 1.0000 2.000 0.4157 0.00951 0.00297 -0.0206 0.3365 1.0000 2.500 0.4665 0.01013 0.00319 -0.0196 0.2719 1.0000 3.000 0.5187 0.01081 0.00351 -0.0190 0.2168 1.0000 3.500 0.5715 0.01152 0.00394 -0.0184 0.1837 1.0000 4.000 0.6243 0.01232 0.00449 -0.0179 0.1621 1.0000 4.500 0.6778 0.01303 0.00509 -0.0175 0.1480 1.0000 5.000 0.7314 0.01374 0.00582 -0.0170 0.1377 1.0000 5.500 0.7834 0.01475 0.00671 -0.0164 0.1293 1.0000 6.000 0.8367 0.01550 0.00748 -0.0159 0.1231 1.0000 6.500 0.8885 0.01652 0.00843 -0.0154 0.1177 1.0000 7.000 0.9397 0.01787 0.00980 -0.0147 0.1138 1.0000 7.500 0.9916 0.01889 0.01093 -0.0141 0.1103 1.0000 8.000 1.0426 0.01989 0.01210 -0.0135 0.1060 1.0000 8.500 1.0919 0.02135 0.01355 -0.0129 0.1021 1.0000 9.000 1.1391 0.02377 0.01615 -0.0121 0.0994 1.0000 9.500 1.1867 0.02543 0.01803 -0.0112 0.0979 1.0000 10.000 1.2319 0.02746 0.02032 -0.0101 0.0963 1.0000 10.500 1.2744 0.02978 0.02292 -0.0089 0.0948 1.0000 11.000 1.3135 0.03236 0.02579 -0.0075 0.0933 1.0000 11.500 1.3481 0.03514 0.02903 -0.0058 0.0917 1.0000 12.000 1.3781 0.03798 0.03218 -0.0037 0.0900 1.0000 12.500 1.4098 0.04008 0.03439 -0.0019 0.0877 1.0000 13.000 1.4036 0.04678 0.04153 0.0017 0.0847 1.0000 13.500 1.4010 0.04913 0.04421 0.0062 0.0832 1.0000 14.000 1.3687 0.05586 0.05138 0.0081 0.0820 1.0000