XFOIL Version 6.94 Calculated polar for: EPPLER 434 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 0.4449 0.01166 0.00648 -0.0843 0.7228 0.9423 0.500 0.5650 0.01195 0.00653 -0.0970 0.7162 0.9581 1.000 0.6246 0.01192 0.00646 -0.0984 0.7068 0.9663 1.500 0.6865 0.01179 0.00621 -0.1001 0.6982 0.9718 2.000 0.7519 0.01176 0.00617 -0.1028 0.6885 0.9762 2.500 0.8134 0.01165 0.00602 -0.1045 0.6782 0.9813 3.000 0.8679 0.01166 0.00601 -0.1048 0.6679 0.9866 3.500 0.9296 0.01152 0.00590 -0.1067 0.6557 0.9909 4.000 0.9899 0.01147 0.00588 -0.1083 0.6430 0.9955 4.500 1.0521 0.01138 0.00578 -0.1102 0.6290 1.0000 5.000 1.0808 0.01145 0.00596 -0.1053 0.6135 1.0000 5.500 1.1091 0.01152 0.00608 -0.1003 0.5972 1.0000 6.000 1.1318 0.01161 0.00618 -0.0942 0.5791 1.0000 6.500 1.1532 0.01174 0.00634 -0.0878 0.5583 1.0000 7.000 1.1874 0.01202 0.00666 -0.0841 0.5322 1.0000 7.500 1.2205 0.01245 0.00708 -0.0803 0.5004 1.0000 8.000 1.2434 0.01307 0.00764 -0.0746 0.4647 1.0000 8.500 1.2583 0.01402 0.00848 -0.0678 0.4255 1.0000 9.000 1.2689 0.01530 0.00964 -0.0608 0.3841 1.0000 9.500 1.2764 0.01695 0.01119 -0.0541 0.3423 1.0000 10.000 1.2821 0.01899 0.01313 -0.0480 0.3015 1.0000 10.500 1.2872 0.02139 0.01543 -0.0425 0.2628 1.0000 11.000 1.2915 0.02416 0.01810 -0.0376 0.2268 1.0000 11.500 1.2953 0.02725 0.02109 -0.0333 0.1925 1.0000 12.000 1.3016 0.03046 0.02425 -0.0298 0.1608 1.0000 12.500 1.3059 0.03407 0.02782 -0.0267 0.1329 1.0000 13.000 1.3087 0.03809 0.03180 -0.0240 0.1087 1.0000 13.500 1.3102 0.04253 0.03621 -0.0218 0.0878 1.0000 14.000 1.3120 0.04728 0.04098 -0.0202 0.0699 1.0000 14.500 1.3130 0.05244 0.04619 -0.0191 0.0560 1.0000 15.000 1.3125 0.05810 0.05194 -0.0186 0.0454 1.0000 15.500 1.3116 0.06415 0.05808 -0.0188 0.0372 1.0000 16.000 1.3133 0.07025 0.06432 -0.0194 0.0299 1.0000 16.500 1.3114 0.07712 0.07137 -0.0207 0.0249 1.0000 17.000 1.3067 0.08477 0.07919 -0.0227 0.0206 1.0000 17.500 1.2996 0.09312 0.08775 -0.0253 0.0173 1.0000 18.000 1.2884 0.10254 0.09739 -0.0288 0.0142 1.0000 18.500 1.2736 0.11294 0.10803 -0.0332 0.0111 1.0000 19.000 1.2539 0.12458 0.11991 -0.0387 0.0084 1.0000 19.500 1.2344 0.13646 0.13199 -0.0450 0.0070 1.0000 20.000 1.2188 0.14782 0.14362 -0.0512 0.0058 1.0000 20.500 1.2052 0.15887 0.15484 -0.0577 0.0053 1.0000 21.000 1.1935 0.16945 0.16558 -0.0641 0.0049 1.0000 21.500 1.1852 0.17953 0.17591 -0.0704 0.0045 1.0000 22.000 1.1780 0.18947 0.18606 -0.0768 0.0043 1.0000 22.500 1.1698 0.19984 0.19662 -0.0835 0.0041 1.0000 23.000 1.1600 0.21086 0.20785 -0.0907 0.0040 1.0000 23.500 1.1442 0.22413 0.22135 -0.0991 0.0040 1.0000 24.000 1.0800 0.25720 0.25467 -0.1149 0.0050 1.0000 26.000 0.8818 0.34384 0.34206 -0.1464 0.0116 1.0000 26.500 0.8864 0.35519 0.35341 -0.1503 0.0113 1.0000 27.000 0.8913 0.36631 0.36456 -0.1543 0.0103 1.0000 27.500 0.8971 0.37602 0.37429 -0.1578 0.0096 1.0000 28.000 0.9042 0.38414 0.38245 -0.1606 0.0091 1.0000 28.500 0.9075 0.39639 0.39471 -0.1647 0.0089 1.0000 29.000 0.9121 0.40756 0.40591 -0.1684 0.0082 1.0000 29.500 0.9168 0.41768 0.41606 -0.1718 0.0077 1.0000 30.000 0.9212 0.42726 0.42566 -0.1751 0.0072 1.0000 30.500 0.9263 0.43599 0.43444 -0.1778 0.0069 1.0000 31.000 0.9286 0.44826 0.44671 -0.1817 0.0068 1.0000 31.500 0.9321 0.45952 0.45800 -0.1851 0.0065 1.0000 32.000 0.9352 0.47003 0.46854 -0.1883 0.0060 1.0000 32.500 0.9380 0.48032 0.47885 -0.1915 0.0056 1.0000 33.000 0.9404 0.48874 0.48732 -0.1944 0.0051 1.0000 34.000 0.9445 0.51225 0.51086 -0.2008 0.0045 1.0000 34.500 0.9461 0.52258 0.52122 -0.2039 0.0041 1.0000 35.000 0.9472 0.53264 0.53131 -0.2069 0.0037 1.0000 35.500 0.9477 0.54202 0.54071 -0.2098 0.0035 1.0000 36.500 0.9481 0.56278 0.56152 -0.2156 0.0034 1.0000 37.000 0.9483 0.57356 0.57233 -0.2184 0.0033 1.0000 37.500 0.9483 0.58407 0.58287 -0.2212 0.0030 1.0000 38.000 0.9474 0.59355 0.59237 -0.2239 0.0029 1.0000 38.500 0.9463 0.60318 0.60204 -0.2266 0.0027 1.0000 39.000 0.9448 0.61247 0.61136 -0.2293 0.0026 1.0000 39.500 0.9430 0.62156 0.62047 -0.2320 0.0024 1.0000 40.000 0.9407 0.63021 0.62916 -0.2345 0.0023 1.0000 40.500 0.9380 0.63849 0.63747 -0.2371 0.0022 1.0000 41.000 0.9348 0.64652 0.64553 -0.2396 0.0021 1.0000 41.500 0.9312 0.65421 0.65325 -0.2421 0.0021 1.0000