XFOIL Version 6.94 Calculated polar for: woubair3 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 -0.0319 0.04118 0.02734 -0.0232 0.9988 0.3497 -2.750 -0.0057 0.04141 0.02778 -0.0229 0.9988 0.3719 -2.500 0.0205 0.04169 0.02819 -0.0225 0.9988 0.3849 -2.250 0.0464 0.04194 0.02868 -0.0222 0.9988 0.4049 -2.000 0.0724 0.04220 0.02919 -0.0219 0.9988 0.4211 -1.750 0.0982 0.04243 0.02978 -0.0216 0.9988 0.4471 -1.500 0.1243 0.04268 0.03037 -0.0213 0.9988 0.4656 -1.250 0.1508 0.04286 0.03102 -0.0211 0.9988 0.4921 -1.000 0.1788 0.04291 0.03177 -0.0209 0.9988 0.5249 -0.750 0.2553 0.03668 0.02715 -0.0284 0.8086 0.5965 -0.250 0.4219 0.03439 0.02239 -0.0458 0.3950 1.0012 0.000 0.4716 0.03543 0.02280 -0.0501 0.3773 1.0012 0.250 0.5200 0.03648 0.02357 -0.0541 0.3640 1.0012 0.500 0.5675 0.03781 0.02471 -0.0580 0.3488 1.0012 0.750 0.6162 0.03956 0.02624 -0.0623 0.3357 1.0012 1.000 0.6547 0.04103 0.02785 -0.0643 0.3231 1.0012 1.250 0.6926 0.04316 0.02997 -0.0664 0.3127 1.0012 1.500 0.7244 0.04502 0.03208 -0.0671 0.3032 1.0012 1.750 0.7543 0.04779 0.03467 -0.0678 0.2936 1.0012 2.000 0.7844 0.05013 0.03741 -0.0683 0.2910 1.0012 2.250 0.8127 0.05271 0.04036 -0.0686 0.2882 1.0012 2.500 0.8385 0.05539 0.04340 -0.0686 0.2839 1.0012 2.750 0.8632 0.05843 0.04675 -0.0686 0.2827 1.0012 3.000 0.8874 0.06206 0.05074 -0.0689 0.2880 1.0012 3.250 0.9120 0.06636 0.05515 -0.0692 0.2933 1.0012 3.500 0.9307 0.07016 0.05973 -0.0699 0.3107 1.0012 3.750 0.9471 0.07482 0.06493 -0.0711 0.3315 1.0012 4.250 0.7147 0.10366 0.09524 -0.0876 0.6413 1.0012 4.500 0.4919 0.11416 0.10567 -0.0727 0.9248 1.0012 4.750 0.4934 0.11924 0.11069 -0.0729 0.9504 1.0012 5.000 0.5090 0.12169 0.11311 -0.0751 0.9259 1.0012