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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2435 0.01319 0.00774 -0.0404 0.6637 0.7707 0.500 0.2956 0.01303 0.00759 -0.0403 0.6566 0.7726 1.000 0.3493 0.01292 0.00746 -0.0404 0.6492 0.7748 1.500 0.4053 0.01286 0.00731 -0.0413 0.6413 0.7768 2.000 0.4569 0.01264 0.00713 -0.0413 0.6333 0.7792 2.500 0.5113 0.01249 0.00694 -0.0418 0.6247 0.7819 3.000 0.5662 0.01240 0.00685 -0.0425 0.6160 0.7840 3.500 0.6198 0.01226 0.00673 -0.0429 0.6064 0.7858 4.000 0.6757 0.01228 0.00673 -0.0437 0.5965 0.7872 4.500 0.7245 0.01200 0.00656 -0.0429 0.5853 0.7894 5.000 0.7758 0.01198 0.00657 -0.0425 0.5733 0.7913 5.500 0.8243 0.01189 0.00659 -0.0416 0.5596 0.7930 6.000 0.8715 0.01188 0.00667 -0.0404 0.5441 0.7948 6.500 0.9160 0.01188 0.00675 -0.0387 0.5244 0.7969 7.000 0.9560 0.01194 0.00686 -0.0362 0.4992 0.7991 7.500 0.9869 0.01214 0.00704 -0.0319 0.4650 0.8016 8.000 1.0014 0.01258 0.00736 -0.0245 0.4174 0.8044 8.500 1.0048 0.01370 0.00823 -0.0157 0.3614 0.8072 9.000 1.0069 0.01491 0.00928 -0.0075 0.3086 0.8103 9.500 1.0061 0.01654 0.01075 0.0004 0.2603 0.8134 10.000 1.0070 0.01846 0.01253 0.0071 0.2179 0.8166 10.500 1.0107 0.02059 0.01456 0.0127 0.1810 0.8200 11.000 1.0156 0.02297 0.01684 0.0174 0.1485 0.8234 11.500 1.0213 0.02557 0.01936 0.0214 0.1198 0.8265 12.000 1.0264 0.02835 0.02208 0.0250 0.0945 0.8302 12.500 1.0309 0.03138 0.02507 0.0282 0.0734 0.8345 13.000 1.0363 0.03465 0.02834 0.0308 0.0567 0.8386 13.500 1.0426 0.03814 0.03185 0.0328 0.0443 0.8428 14.000 1.0492 0.04190 0.03565 0.0342 0.0355 0.8468 14.500 1.0557 0.04578 0.03966 0.0353 0.0289 0.8518 15.000 1.0613 0.04999 0.04401 0.0361 0.0239 0.8574 15.500 1.0652 0.05470 0.04884 0.0362 0.0197 0.8635 16.000 1.0653 0.06011 0.05441 0.0359 0.0164 0.8701 16.500 1.0645 0.06584 0.06037 0.0352 0.0137 0.8791 17.000 1.0610 0.07233 0.06708 0.0338 0.0112 0.8907 17.500 1.0581 0.07923 0.07431 0.0317 0.0096 0.9153