XFOIL Version 6.94 Calculated polar for: EPPLER EC 86(-3)-914 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 0.5243 0.01768 0.01251 -0.1500 0.8499 0.6480 0.500 0.6011 0.01681 0.01172 -0.1517 0.8436 0.6986 1.500 0.7017 0.01591 0.01108 -0.1454 0.8233 0.7425 2.000 0.7401 0.01551 0.01078 -0.1406 0.8053 0.7529 3.000 0.8578 0.01412 0.00942 -0.1395 0.7568 0.7746 4.500 0.9858 0.01597 0.00960 -0.1314 0.4444 0.7966 5.000 1.0169 0.01741 0.01056 -0.1281 0.3576 0.8005 5.500 1.0532 0.01895 0.01157 -0.1262 0.2767 0.8031 6.000 1.0968 0.01984 0.01233 -0.1251 0.2414 0.8056 6.500 1.1387 0.02066 0.01313 -0.1234 0.2199 0.8084 7.000 1.1788 0.02181 0.01410 -0.1218 0.1838 0.8108 7.500 1.2225 0.02278 0.01507 -0.1208 0.1661 0.8134 8.000 1.2654 0.02386 0.01616 -0.1197 0.1488 0.8161 8.500 1.2825 0.02725 0.01876 -0.1156 0.0342 0.8190 9.000 1.3153 0.02943 0.02089 -0.1135 0.0104 0.8221 9.500 1.3475 0.03151 0.02307 -0.1113 0.0021 0.8244 10.000 1.3786 0.03342 0.02522 -0.1088 0.0019 0.8269 10.500 1.4060 0.03572 0.02777 -0.1061 0.0019 0.8298 11.000 1.4294 0.03849 0.03083 -0.1032 0.0019 0.8329 11.500 1.4473 0.04196 0.03461 -0.1003 0.0020 0.8361 12.000 1.4577 0.04636 0.03936 -0.0973 0.0021 0.8394 12.500 1.4590 0.05197 0.04531 -0.0945 0.0021 0.8428 13.000 1.4503 0.05889 0.05259 -0.0921 0.0022 0.8459 13.500 1.4354 0.06752 0.06157 -0.0913 0.0023 0.8488 14.000 1.4161 0.07781 0.07220 -0.0924 0.0023 0.8516 14.500 1.4047 0.08793 0.08264 -0.0950 0.0024 0.8546 15.000 1.3932 0.09878 0.09379 -0.0988 0.0025 0.8574 15.500 1.3816 0.10986 0.10519 -0.1029 0.0027 0.8599 16.000 1.3737 0.11992 0.11555 -0.1064 0.0030 0.8625 16.500 1.3685 0.12956 0.12553 -0.1099 0.0033 0.8656 17.000 1.3612 0.14003 0.13634 -0.1149 0.0036 0.8692 17.500 1.3521 0.15114 0.14776 -0.1212 0.0038 0.8731 18.000 1.3441 0.16273 0.15969 -0.1289 0.0041 0.8773 18.500 1.3173 0.17979 0.17728 -0.1410 0.0043 0.8816 19.000 1.2960 0.19621 0.19404 -0.1533 0.0044 0.8872 19.500 1.2708 0.21525 0.21339 -0.1673 0.0044 0.8923 20.000 1.2522 0.23328 0.23162 -0.1799 0.0043 0.8985 21.000 0.9432 0.30348 0.30214 -0.1782 0.0140 0.8417 21.500 0.9524 0.31271 0.31139 -0.1807 0.0138 0.8437 22.000 0.9499 0.32887 0.32754 -0.1866 0.0130 0.8449 22.500 0.9558 0.34001 0.33870 -0.1901 0.0120 0.8471 23.000 0.9632 0.35009 0.34880 -0.1933 0.0113 0.8496 24.000 0.9762 0.37402 0.37276 -0.2007 0.0106 0.8549 24.500 0.9831 0.38723 0.38598 -0.2048 0.0096 0.8576 25.000 0.9902 0.39806 0.39683 -0.2082 0.0087 0.8603 25.500 0.9956 0.40748 0.40628 -0.2105 0.0084 0.8635 26.000 1.0009 0.41870 0.41752 -0.2133 0.0082 0.8670 26.500 1.0049 0.43313 0.43195 -0.2175 0.0075 0.8701 27.000 1.0111 0.44542 0.44426 -0.2210 0.0068 0.8742 27.500 1.0150 0.45568 0.45455 -0.2236 0.0063 0.8785 28.000 1.0188 0.46486 0.46376 -0.2257 0.0060 0.8836 28.500 1.0231 0.47801 0.47691 -0.2289 0.0058 0.8881 29.000 1.0267 0.49179 0.49071 -0.2325 0.0054 0.8920 29.500 1.0284 0.50183 0.50077 -0.2346 0.0049 0.8975 30.000 1.0318 0.51340 0.51236 -0.2376 0.0045 0.9035 30.500 1.0326 0.52264 0.52162 -0.2396 0.0042 0.9098 31.000 1.0340 0.53202 0.53103 -0.2417 0.0040 0.9177 31.500 1.0324 0.53999 0.53901 -0.2428 0.0039 0.9271 32.000 1.0304 0.54889 0.54790 -0.2445 0.0038 0.9378 32.500 1.0245 0.55287 0.55187 -0.2441 0.0036 0.9581 33.000 1.0228 0.56022 0.55923 -0.2455 0.0034 1.0000 33.500 1.0266 0.57387 0.57290 -0.2493 0.0031 1.0000 34.000 1.0297 0.58735 0.58641 -0.2530 0.0029 1.0000 34.500 1.0321 0.60037 0.59944 -0.2565 0.0026 1.0000 35.000 1.0338 0.61261 0.61171 -0.2598 0.0025 1.0000 35.500 1.0345 0.62422 0.62335 -0.2630 0.0024 1.0000 36.500 1.0346 0.64835 0.64751 -0.2687 0.0023 1.0000 37.000 1.0339 0.65990 0.65907 -0.2715 0.0023 1.0000 37.500 1.0326 0.67086 0.67006 -0.2742 0.0023 1.0000 38.000 1.0311 0.68206 0.68127 -0.2768 0.0023 1.0000 38.500 1.0290 0.69236 0.69159 -0.2792 0.0023 1.0000 39.000 1.0268 0.70273 0.70197 -0.2816 0.0022 1.0000 39.500 1.0233 0.71151 0.71078 -0.2838 0.0022 1.0000 40.000 1.0200 0.72060 0.71989 -0.2860 0.0022 1.0000 40.500 1.0161 0.72926 0.72857 -0.2881 0.0022 1.0000 41.000 1.0121 0.73786 0.73719 -0.2901 0.0022 1.0000 41.500 1.0071 0.74501 0.74436 -0.2921 0.0022 1.0000 42.000 1.0026 0.75322 0.75259 -0.2940 0.0022 1.0000 42.500 0.9970 0.75969 0.75908 -0.2959 0.0023 1.0000 43.000 0.9913 0.76612 0.76553 -0.2977 0.0023 1.0000 43.500 0.9853 0.77243 0.77186 -0.2994 0.0023 1.0000 44.000 0.9790 0.77808 0.77754 -0.3012 0.0023 1.0000 44.500 0.9724 0.78339 0.78286 -0.3028 0.0023 1.0000 45.000 0.9654 0.78802 0.78751 -0.3043 0.0023 1.0000 45.500 0.9581 0.79205 0.79157 -0.3059 0.0023 1.0000 46.000 0.9508 0.79644 0.79597 -0.3074 0.0023 1.0000