XFOIL Version 6.94 Calculated polar for: EPPLER 543 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 0.2841 0.01854 0.01263 -0.0422 0.6918 0.7911 0.500 0.3400 0.01848 0.01247 -0.0427 0.6844 0.7941 1.000 0.3742 0.01807 0.01212 -0.0397 0.6763 0.7984 1.500 0.4078 0.01745 0.01144 -0.0372 0.6683 0.8034 2.000 0.4496 0.01700 0.01092 -0.0366 0.6604 0.8079 2.500 0.4954 0.01659 0.01058 -0.0354 0.6510 0.8096 3.000 0.5502 0.01639 0.01033 -0.0359 0.6425 0.8111 3.500 0.5947 0.01625 0.01032 -0.0343 0.6327 0.8136 4.000 0.6481 0.01599 0.01005 -0.0347 0.6228 0.8154 4.500 0.6952 0.01582 0.00999 -0.0339 0.6117 0.8176 5.000 0.7496 0.01556 0.00974 -0.0345 0.5998 0.8196 5.500 0.7954 0.01536 0.00966 -0.0334 0.5858 0.8225 6.000 0.8464 0.01519 0.00955 -0.0334 0.5716 0.8249 6.500 0.8968 0.01501 0.00941 -0.0331 0.5544 0.8267 7.000 0.9364 0.01475 0.00926 -0.0306 0.5334 0.8287 7.500 0.9674 0.01459 0.00925 -0.0263 0.5079 0.8310 8.000 0.9889 0.01456 0.00932 -0.0201 0.4750 0.8337 8.500 0.9996 0.01490 0.00960 -0.0123 0.4322 0.8374 9.000 1.0016 0.01591 0.01042 -0.0038 0.3794 0.8415 9.500 0.9996 0.01741 0.01173 0.0042 0.3265 0.8451 10.000 0.9946 0.01939 0.01351 0.0116 0.2781 0.8484 10.500 0.9899 0.02161 0.01562 0.0183 0.2353 0.8524 11.000 0.9880 0.02417 0.01809 0.0236 0.1962 0.8566 11.500 0.9888 0.02700 0.02083 0.0279 0.1612 0.8611 12.000 0.9912 0.03007 0.02383 0.0313 0.1304 0.8661 12.500 0.9932 0.03334 0.02706 0.0343 0.1041 0.8710 13.000 0.9946 0.03692 0.03062 0.0369 0.0824 0.8764 13.500 0.9968 0.04083 0.03453 0.0388 0.0652 0.8823 14.000 1.0002 0.04498 0.03874 0.0400 0.0521 0.8885 14.500 1.0023 0.04931 0.04320 0.0411 0.0427 0.8968 16.500 1.0229 0.07195 0.06656 0.0341 0.0209 1.0000 17.500 1.0193 0.08648 0.08139 0.0285 0.0152 1.0000 18.000 1.0159 0.09418 0.08917 0.0252 0.0134 1.0000 18.500 1.0132 0.10223 0.09749 0.0216 0.0120 1.0000 19.000 1.0108 0.11005 0.10540 0.0178 0.0109 1.0000 19.500 1.0018 0.11964 0.11532 0.0127 0.0099 1.0000 20.000 0.9965 0.12849 0.12434 0.0077 0.0092 1.0000 20.500 0.9941 0.13641 0.13237 0.0033 0.0087 1.0000 21.000 0.9800 0.14734 0.14362 -0.0032 0.0085 1.0000 21.500 0.9589 0.16002 0.15664 -0.0110 0.0084 1.0000 22.000 0.9359 0.17351 0.17042 -0.0194 0.0084 1.0000 22.500 0.9045 0.18975 0.18692 -0.0291 0.0086 1.0000