XFOIL Version 6.94 Calculated polar for: ARA-D BL 12% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1785 0.04099 0.03285 -0.0200 1.0000 0.2630 -2.750 -0.1586 0.03930 0.03124 -0.0194 1.0000 0.2713 -2.500 -0.1335 0.03791 0.02958 -0.0198 1.0000 0.2816 -2.250 -0.1104 0.03650 0.02816 -0.0197 1.0000 0.2930 -2.000 -0.0855 0.03560 0.02710 -0.0198 1.0000 0.3076 -1.750 -0.0615 0.03467 0.02629 -0.0197 1.0000 0.3246 -1.500 0.1594 0.02664 0.01886 -0.0375 0.6890 0.4682 -1.250 0.1715 0.02679 0.01780 -0.0299 0.4687 0.5292 -0.750 0.2479 0.02672 0.01713 -0.0286 0.3774 1.0000 -0.500 0.2767 0.02778 0.01755 -0.0281 0.3577 1.0000 -0.250 0.3060 0.02889 0.01817 -0.0277 0.3433 1.0000 0.000 0.3362 0.02998 0.01899 -0.0275 0.3332 1.0000 0.250 0.3664 0.03130 0.01998 -0.0273 0.3260 1.0000 0.500 0.3966 0.03256 0.02124 -0.0273 0.3202 1.0000 0.750 0.4256 0.03395 0.02253 -0.0273 0.3143 1.0000 1.000 0.4537 0.03553 0.02386 -0.0270 0.3083 1.0000 1.250 0.4812 0.03723 0.02560 -0.0271 0.3034 1.0000 1.500 0.5083 0.03903 0.02754 -0.0272 0.2997 1.0000 1.750 0.5348 0.04111 0.02975 -0.0275 0.2984 1.0000 2.000 0.5603 0.04345 0.03224 -0.0279 0.2980 1.0000 2.250 0.5844 0.04609 0.03504 -0.0284 0.2985 1.0000 2.500 0.6060 0.04903 0.03817 -0.0290 0.2990 1.0000 2.750 0.6249 0.05230 0.04163 -0.0298 0.2994 1.0000 3.000 0.6409 0.05594 0.04546 -0.0307 0.3003 1.0000 3.250 0.6549 0.05991 0.04956 -0.0316 0.3025 1.0000 3.500 0.6649 0.06463 0.05450 -0.0334 0.3092 1.0000 3.750 0.6500 0.07333 0.06362 -0.0390 0.3298 1.0000 4.500 0.4132 0.10838 0.09953 -0.0769 0.6563 1.0000 4.750 0.4306 0.11258 0.10360 -0.0777 0.6475 1.0000 5.000 0.4434 0.11515 0.10606 -0.0772 0.6299 1.0000