XFOIL Version 6.94 Calculated polar for: RG 8 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 0.3563 0.00836 0.00335 -0.0889 0.8724 0.7424 0.500 0.4151 0.00824 0.00323 -0.0889 0.8418 0.7640 1.000 0.4749 0.00819 0.00312 -0.0891 0.8087 0.7853 1.500 0.5285 0.00823 0.00312 -0.0881 0.7703 0.8065 2.000 0.5790 0.00833 0.00316 -0.0864 0.7288 0.8301 2.500 0.6262 0.00847 0.00326 -0.0841 0.6850 0.8587 3.000 0.6683 0.00862 0.00337 -0.0806 0.6398 0.8991 3.500 0.7198 0.00876 0.00350 -0.0793 0.5900 0.9719 4.000 0.7753 0.00925 0.00374 -0.0796 0.5363 1.0000 4.500 0.8208 0.00990 0.00408 -0.0777 0.4642 1.0000 5.000 0.8644 0.01068 0.00452 -0.0756 0.3900 1.0000 5.500 0.9058 0.01167 0.00509 -0.0732 0.3047 1.0000 6.000 0.9499 0.01259 0.00576 -0.0713 0.2422 1.0000 6.500 0.9909 0.01376 0.00659 -0.0690 0.1713 1.0000 7.000 1.0299 0.01513 0.00759 -0.0665 0.1062 1.0000 7.500 1.0700 0.01635 0.00866 -0.0641 0.0693 1.0000 8.000 1.1071 0.01773 0.00990 -0.0612 0.0380 1.0000 8.500 1.1383 0.01948 0.01152 -0.0574 0.0129 1.0000 9.000 1.1665 0.02110 0.01326 -0.0528 0.0071 1.0000 9.500 1.1913 0.02283 0.01518 -0.0479 0.0060 1.0000 10.000 1.2133 0.02472 0.01733 -0.0430 0.0056 1.0000 10.500 1.2289 0.02700 0.01988 -0.0376 0.0054 1.0000 11.000 1.2384 0.02973 0.02287 -0.0322 0.0052 1.0000 11.500 1.2411 0.03315 0.02656 -0.0271 0.0051 1.0000 12.000 1.2400 0.03728 0.03097 -0.0230 0.0051 1.0000 12.500 1.2348 0.04235 0.03633 -0.0200 0.0050 1.0000 13.000 1.2276 0.04835 0.04265 -0.0186 0.0051 1.0000 13.500 1.2166 0.05558 0.05023 -0.0186 0.0051 1.0000 14.000 1.2019 0.06418 0.05919 -0.0204 0.0051 1.0000 14.500 1.1820 0.07457 0.06998 -0.0241 0.0052 1.0000 15.000 1.1565 0.08713 0.08295 -0.0301 0.0053 1.0000 15.500 1.1269 0.10188 0.09810 -0.0384 0.0054 1.0000 16.000 1.0963 0.11830 0.11487 -0.0484 0.0056 1.0000 16.500 1.0636 0.13667 0.13356 -0.0599 0.0057 1.0000 17.000 1.0296 0.15691 0.15406 -0.0725 0.0059 1.0000 17.500 0.9931 0.17976 0.17707 -0.0857 0.0062 1.0000