XFOIL Version 6.94 Calculated polar for: EPPLER 593 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3042 0.01153 0.00413 -0.0333 0.4570 0.2460 0.500 0.3464 0.00971 0.00418 -0.0306 0.4537 0.8364 1.500 0.4967 0.01027 0.00468 -0.0378 0.4469 1.0000 2.000 0.5506 0.01050 0.00486 -0.0372 0.4442 1.0000 2.500 0.6048 0.01072 0.00503 -0.0366 0.4406 1.0000 3.000 0.6592 0.01095 0.00523 -0.0361 0.4370 1.0000 3.500 0.7138 0.01119 0.00542 -0.0356 0.4337 1.0000 4.000 0.7686 0.01144 0.00561 -0.0352 0.4301 1.0000 4.500 0.8224 0.01207 0.00625 -0.0349 0.4255 1.0000 5.000 0.8776 0.01215 0.00641 -0.0346 0.4218 1.0000 5.500 0.9327 0.01227 0.00660 -0.0343 0.4167 1.0000 6.000 0.9881 0.01230 0.00665 -0.0341 0.4116 1.0000 6.500 1.0432 0.01241 0.00673 -0.0338 0.4060 1.0000 7.000 1.0977 0.01260 0.00707 -0.0336 0.4002 1.0000 7.500 1.1527 0.01258 0.00718 -0.0334 0.3932 1.0000 8.000 1.2080 0.01244 0.00706 -0.0331 0.3853 1.0000 8.500 1.2621 0.01253 0.00732 -0.0329 0.3759 1.0000 9.000 1.3164 0.01245 0.00733 -0.0326 0.3637 1.0000 9.500 1.3696 0.01259 0.00765 -0.0324 0.3470 1.0000 10.000 1.4206 0.01294 0.00804 -0.0319 0.3214 1.0000 10.500 1.4647 0.01400 0.00900 -0.0310 0.2753 1.0000 11.000 1.4969 0.01612 0.01094 -0.0292 0.2203 1.0000 11.500 1.5158 0.01888 0.01356 -0.0264 0.1772 1.0000 12.000 1.5129 0.02210 0.01678 -0.0215 0.1491 1.0000 12.500 1.4746 0.02955 0.02439 -0.0201 0.1369 1.0000 13.000 1.4425 0.03734 0.03225 -0.0197 0.1245 1.0000 13.500 1.4146 0.04474 0.03967 -0.0195 0.1121 1.0000 14.000 1.3936 0.05173 0.04668 -0.0197 0.0997 1.0000 14.500 1.3807 0.05855 0.05354 -0.0206 0.0875 1.0000 15.000 1.3717 0.06540 0.06043 -0.0218 0.0757 1.0000 15.500 1.3656 0.07220 0.06726 -0.0233 0.0652 1.0000 16.000 1.3583 0.07954 0.07465 -0.0253 0.0564 1.0000 16.500 1.3512 0.08717 0.08234 -0.0276 0.0487 1.0000 17.500 1.3396 0.10297 0.09829 -0.0332 0.0356 1.0000 18.000 1.3334 0.11142 0.10685 -0.0367 0.0307 1.0000 18.500 1.3286 0.11978 0.11533 -0.0404 0.0263 1.0000 19.000 1.3218 0.12881 0.12447 -0.0447 0.0229 1.0000 19.500 1.3148 0.13800 0.13377 -0.0495 0.0197 1.0000 20.000 1.3112 0.14673 0.14268 -0.0541 0.0175 1.0000 20.500 1.3052 0.15600 0.15210 -0.0594 0.0155 1.0000 21.000 1.2992 0.16536 0.16158 -0.0651 0.0140 1.0000 21.500 1.2954 0.17433 0.17073 -0.0707 0.0124 1.0000 22.000 1.2885 0.18402 0.18051 -0.0769 0.0112 1.0000 22.500 1.2844 0.19325 0.18993 -0.0831 0.0098 1.0000 23.000 1.2776 0.20310 0.19985 -0.0899 0.0086 1.0000 23.500 1.2726 0.21278 0.20972 -0.0966 0.0074 1.0000 24.000 1.2667 0.22260 0.21962 -0.1036 0.0064 1.0000 24.500 1.2612 0.23270 0.22989 -0.1107 0.0055 1.0000 25.000 1.2585 0.24189 0.23912 -0.1174 0.0047 1.0000 25.500 1.2539 0.25200 0.24942 -0.1245 0.0042 1.0000 26.000 1.2495 0.26218 0.25974 -0.1316 0.0038 1.0000 26.500 1.2472 0.27187 0.26952 -0.1385 0.0035 1.0000 27.000 1.2407 0.28331 0.28106 -0.1461 0.0032 1.0000 28.000 1.2039 0.34158 0.33923 -0.1667 0.0073 1.0000 28.500 1.2150 0.34655 0.34422 -0.1709 0.0069 1.0000 29.000 1.2265 0.35054 0.34824 -0.1747 0.0067 1.0000 29.500 1.2373 0.35600 0.35371 -0.1788 0.0065 1.0000 30.000 1.2471 0.36478 0.36246 -0.1844 0.0060 1.0000 30.500 1.2574 0.37023 0.36792 -0.1888 0.0055 1.0000 31.000 1.2675 0.37508 0.37280 -0.1932 0.0052 1.0000 31.500 1.2768 0.37904 0.37678 -0.1975 0.0049 1.0000 32.500 1.2955 0.39020 0.38796 -0.2066 0.0045 1.0000 33.000 1.3046 0.39542 0.39318 -0.2110 0.0040 1.0000 33.500 1.3130 0.39978 0.39757 -0.2154 0.0035 1.0000 34.000 1.3207 0.40356 0.40137 -0.2199 0.0033 1.0000 34.500 1.3272 0.40625 0.40410 -0.2238 0.0032 1.0000 35.000 1.3349 0.41144 0.40928 -0.2284 0.0031 1.0000 35.500 1.3440 0.41811 0.41595 -0.2333 0.0028 1.0000 36.000 1.3510 0.42240 0.42026 -0.2377 0.0024 1.0000 36.500 1.3572 0.42625 0.42413 -0.2422 0.0022 1.0000 37.000 1.3628 0.42983 0.42774 -0.2467 0.0021 1.0000 37.500 1.3674 0.43281 0.43074 -0.2511 0.0020 1.0000 38.000 1.3711 0.43520 0.43317 -0.2553 0.0019 1.0000 38.500 1.3758 0.43857 0.43655 -0.2597 0.0019 1.0000 39.000 1.3805 0.44222 0.44021 -0.2644 0.0018 1.0000 39.500 1.3847 0.44537 0.44338 -0.2690 0.0018 1.0000 40.000 1.3895 0.44888 0.44690 -0.2737 0.0018 1.0000