XFOIL Version 6.94 Calculated polar for: EPPLER 68 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 0.4575 0.00933 0.00410 -0.1119 0.8007 0.7856 0.500 0.5100 0.00930 0.00410 -0.1107 0.7869 0.8256 1.000 0.5585 0.00931 0.00415 -0.1086 0.7717 0.8635 1.500 0.6035 0.00929 0.00418 -0.1056 0.7552 0.9001 2.000 0.6499 0.00924 0.00412 -0.1028 0.7389 0.9381 2.500 0.7160 0.00923 0.00412 -0.1048 0.7199 0.9728 3.000 0.8011 0.00929 0.00414 -0.1112 0.6988 0.9986 3.500 0.8419 0.00945 0.00424 -0.1086 0.6774 1.0000 4.000 0.8899 0.00966 0.00441 -0.1072 0.6537 1.0000 4.500 0.9382 0.00993 0.00462 -0.1058 0.6274 1.0000 5.000 0.9857 0.01025 0.00490 -0.1041 0.5990 1.0000 5.500 1.0306 0.01064 0.00523 -0.1020 0.5666 1.0000 6.000 1.0727 0.01111 0.00566 -0.0994 0.5299 1.0000 6.500 1.1110 0.01170 0.00617 -0.0961 0.4867 1.0000 7.000 1.1436 0.01247 0.00680 -0.0918 0.4355 1.0000 7.500 1.1676 0.01346 0.00759 -0.0861 0.3773 1.0000 8.000 1.1856 0.01484 0.00868 -0.0797 0.3103 1.0000 8.500 1.2009 0.01660 0.01008 -0.0735 0.2395 1.0000 9.000 1.2182 0.01850 0.01171 -0.0682 0.1804 1.0000 9.500 1.2359 0.02055 0.01354 -0.0634 0.1331 1.0000 10.000 1.2533 0.02278 0.01562 -0.0589 0.0967 1.0000 10.500 1.2675 0.02539 0.01810 -0.0545 0.0629 1.0000 11.000 1.2716 0.02897 0.02155 -0.0495 0.0361 1.0000 11.500 1.2772 0.03269 0.02535 -0.0453 0.0280 1.0000 12.000 1.2809 0.03683 0.02967 -0.0417 0.0248 1.0000 12.500 1.2879 0.04096 0.03397 -0.0389 0.0226 1.0000 13.000 1.2874 0.04610 0.03925 -0.0365 0.0210 1.0000 13.500 1.2948 0.05080 0.04417 -0.0347 0.0198 1.0000 14.000 1.3029 0.05569 0.04928 -0.0334 0.0187 1.0000 14.500 1.3106 0.06085 0.05465 -0.0325 0.0179 1.0000 15.000 1.3177 0.06631 0.06030 -0.0319 0.0172 1.0000 15.500 1.3242 0.07225 0.06643 -0.0311 0.0163 1.0000 16.000 1.3205 0.07972 0.07429 -0.0318 0.0158 1.0000 16.500 1.3109 0.08833 0.08331 -0.0338 0.0155 1.0000 17.000 1.2949 0.09841 0.09381 -0.0371 0.0153 1.0000 17.500 1.2724 0.11018 0.10600 -0.0421 0.0153 1.0000 18.000 1.2434 0.12396 0.12019 -0.0496 0.0152 1.0000 18.500 1.2106 0.13957 0.13619 -0.0593 0.0154 1.0000 19.000 1.1726 0.15784 0.15481 -0.0718 0.0157 1.0000 19.500 1.1283 0.17964 0.17689 -0.0869 0.0161 1.0000