XFOIL Version 6.94 Calculated polar for: EPPLER STE 871-514 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 0.2144 0.01941 0.01531 -0.0588 0.8501 0.8399 0.500 0.2781 0.01906 0.01491 -0.0610 0.8437 0.8429 1.000 0.3536 0.01846 0.01427 -0.0651 0.8409 0.8446 1.500 0.4323 0.01762 0.01342 -0.0696 0.8388 0.8459 2.000 0.5094 0.01631 0.01213 -0.0734 0.8361 0.8473 3.000 0.6513 0.01291 0.00881 -0.0779 0.8182 0.8494 4.000 0.7326 0.01228 0.00829 -0.0725 0.7587 0.8526 4.500 0.8148 0.01087 0.00631 -0.0764 0.6494 0.8529 5.000 0.8262 0.01233 0.00713 -0.0685 0.5218 0.8552 5.500 0.8372 0.01415 0.00828 -0.0615 0.3853 0.8566 6.000 0.8599 0.01584 0.00931 -0.0570 0.2567 0.8577 6.500 0.8893 0.01739 0.01032 -0.0537 0.1579 0.8587 7.000 0.9237 0.01871 0.01134 -0.0513 0.1067 0.8597 7.500 0.9613 0.01984 0.01237 -0.0492 0.0878 0.8612 8.000 0.9979 0.02103 0.01355 -0.0471 0.0778 0.8621 8.500 1.0341 0.02222 0.01477 -0.0450 0.0709 0.8630 9.500 1.1036 0.02484 0.01756 -0.0405 0.0615 0.8648 10.000 1.1362 0.02630 0.01907 -0.0381 0.0578 0.8657 11.000 1.2014 0.02915 0.02213 -0.0338 0.0497 0.8680 11.500 1.2312 0.03065 0.02372 -0.0314 0.0462 0.8696 12.000 1.2604 0.03228 0.02555 -0.0290 0.0433 0.8712 12.500 1.2846 0.03425 0.02759 -0.0263 0.0409 0.8730 13.000 1.3119 0.03600 0.02961 -0.0240 0.0381 0.8753 13.500 1.3333 0.03823 0.03195 -0.0215 0.0359 0.8778 14.000 1.3590 0.04020 0.03417 -0.0196 0.0331 0.8801 14.500 1.3822 0.04250 0.03669 -0.0179 0.0304 0.8825 15.000 1.4128 0.04429 0.03867 -0.0171 0.0260 0.8850 15.500 1.4391 0.04651 0.04101 -0.0160 0.0186 0.8879 16.000 1.4377 0.05137 0.04597 -0.0133 0.0096 0.8915 16.500 1.4283 0.05750 0.05238 -0.0112 0.0075 0.8956 17.000 1.4147 0.06464 0.05982 -0.0104 0.0067 0.9002 17.500 1.3968 0.07301 0.06854 -0.0110 0.0063 0.9053 18.000 1.3729 0.08279 0.07869 -0.0130 0.0061 0.9127 18.500 1.3394 0.09480 0.09108 -0.0170 0.0059 0.9244 19.500 1.2433 0.12690 0.12395 -0.0326 0.0062 0.9980 20.000 1.1789 0.14862 0.14602 -0.0450 0.0067 0.9980 20.500 1.1214 0.17041 0.16812 -0.0580 0.0073 0.9980 21.000 1.0748 0.19145 0.18934 -0.0712 0.0077 0.9980 21.500 1.0581 0.20580 0.20376 -0.0807 0.0075 0.9980 22.000 1.0562 0.21620 0.21420 -0.0879 0.0071 0.9980 22.500 1.0651 0.22298 0.22094 -0.0933 0.0066 0.9980 23.000 1.0622 0.23422 0.23228 -0.1010 0.0064 0.9980