XFOIL Version 6.94 Calculated polar for: nacd632 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2745 0.05037 0.02861 -0.0119 0.9994 1.0006 0.250 0.2921 0.05132 0.02941 -0.0113 0.9994 1.0006 0.500 0.3095 0.05235 0.03030 -0.0109 0.9994 1.0006 0.750 0.3266 0.05347 0.03131 -0.0107 0.9994 1.0006 1.000 0.3433 0.05469 0.03248 -0.0106 0.9994 1.0006 1.250 0.3595 0.05603 0.03381 -0.0106 0.9994 1.0006 1.500 0.3750 0.05750 0.03528 -0.0107 0.9994 1.0006 1.750 0.3895 0.05916 0.03701 -0.0110 0.9994 1.0006 2.000 0.4028 0.06102 0.03899 -0.0115 0.9994 1.0006 2.250 0.4146 0.06316 0.04127 -0.0122 0.9994 1.0006 2.500 0.4245 0.06563 0.04390 -0.0132 0.9994 1.0006 2.750 0.4321 0.06848 0.04692 -0.0145 0.9994 1.0006 3.000 0.4377 0.07170 0.05028 -0.0161 0.9994 1.0006 3.250 0.4422 0.07516 0.05387 -0.0179 0.9994 1.0006 3.500 0.4468 0.07875 0.05754 -0.0199 0.9994 1.0006 3.750 0.4517 0.08236 0.06122 -0.0219 0.9994 1.0006 4.000 0.4571 0.08593 0.06487 -0.0239 0.9994 1.0006 4.250 0.4630 0.08948 0.06847 -0.0258 0.9994 1.0006 4.500 0.4694 0.09299 0.07205 -0.0277 0.9994 1.0006 4.750 0.4762 0.09650 0.07562 -0.0295 0.9994 1.0006 5.000 0.4834 0.09999 0.07916 -0.0313 0.9994 1.0006