XFOIL Version 6.94 Calculated polar for: voyager2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.4883 0.02335 0.01308 0.0232 1.0000 0.0430 -2.750 -0.4682 0.02224 0.01204 0.0246 1.0000 0.0487 -2.500 -0.4484 0.02137 0.01111 0.0262 1.0000 0.0539 -2.250 -0.4272 0.02070 0.01034 0.0277 1.0000 0.0531 -2.000 -0.4048 0.02008 0.00954 0.0290 1.0000 0.0528 -1.750 -0.3817 0.01950 0.00876 0.0301 1.0000 0.0543 -1.500 -0.3584 0.01908 0.00819 0.0312 1.0000 0.0588 -1.250 -0.3361 0.01828 0.00794 0.0322 1.0000 0.2218 -1.000 -0.3137 0.01807 0.00792 0.0331 1.0000 0.2823 -0.750 -0.2942 0.01727 0.00784 0.0341 1.0000 0.4069 -0.250 -0.1671 0.01800 0.01048 0.0236 1.0000 0.9657 0.000 -0.0708 0.01879 0.01107 0.0095 1.0000 0.9878 0.250 0.0040 0.01905 0.01124 -0.0007 0.9996 1.0000 0.500 0.2486 0.01896 0.00733 -0.0395 0.0431 0.9969 0.750 0.2824 0.01901 0.00743 -0.0409 0.0382 1.0000 1.000 0.3055 0.01915 0.00766 -0.0401 0.0378 1.0000 1.250 0.3286 0.01934 0.00800 -0.0392 0.0383 1.0000 1.500 0.3516 0.01956 0.00833 -0.0383 0.0396 1.0000 1.750 0.3744 0.01978 0.00869 -0.0373 0.0416 1.0000 2.000 0.3970 0.02010 0.00918 -0.0362 0.0442 1.0000 2.250 0.4189 0.02055 0.00979 -0.0350 0.0472 1.0000 2.500 0.4393 0.02115 0.01062 -0.0336 0.0496 1.0000 2.750 0.4588 0.02178 0.01131 -0.0319 0.0524 1.0000 3.000 0.4804 0.02205 0.01170 -0.0303 0.0577 1.0000 3.250 0.5015 0.02301 0.01262 -0.0287 0.0633 1.0000 3.500 0.5256 0.02361 0.01323 -0.0274 0.0693 1.0000 3.750 0.5545 0.02479 0.01439 -0.0267 0.0792 1.0000 4.000 0.5819 0.02515 0.01497 -0.0252 0.0907 1.0000 4.250 0.6120 0.02589 0.01594 -0.0241 0.1054 1.0000 4.500 0.6450 0.02715 0.01741 -0.0233 0.1243 1.0000 4.750 0.6750 0.02717 0.01805 -0.0211 0.1483 1.0000 5.000 0.7076 0.02841 0.02015 -0.0193 0.1803 1.0000