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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0301 0.03953 0.02660 -0.0239 0.9988 0.2708 -2.750 -0.0036 0.03983 0.02695 -0.0234 0.9988 0.2884 -2.500 0.0228 0.04012 0.02737 -0.0231 0.9988 0.3067 -2.250 0.0492 0.04040 0.02783 -0.0228 0.9988 0.3223 -2.000 0.0756 0.04067 0.02835 -0.0225 0.9988 0.3365 -1.750 0.1020 0.04096 0.02892 -0.0223 0.9988 0.3547 -1.500 0.1287 0.04122 0.02957 -0.0221 0.9988 0.3748 -1.250 0.1567 0.04142 0.03029 -0.0219 0.9988 0.3959 -1.000 0.3476 0.03391 0.02109 -0.0505 0.3775 0.4945 -0.750 0.3801 0.03426 0.02146 -0.0513 0.3557 0.5370 -0.500 0.4164 0.03424 0.02177 -0.0528 0.3401 0.6005 -0.250 0.4436 0.03252 0.02141 -0.0507 0.3310 0.9521 0.000 0.5001 0.03325 0.02147 -0.0568 0.3188 1.0012 0.250 0.5487 0.03431 0.02222 -0.0611 0.3057 1.0012 0.500 0.5939 0.03583 0.02342 -0.0646 0.2950 1.0012 0.750 0.6289 0.03710 0.02474 -0.0659 0.2842 1.0012 1.000 0.6611 0.03895 0.02641 -0.0670 0.2745 1.0012 1.250 0.6919 0.04063 0.02829 -0.0675 0.2652 1.0012 1.500 0.7225 0.04254 0.03025 -0.0681 0.2571 1.0012 1.750 0.7527 0.04533 0.03295 -0.0688 0.2518 1.0012 2.000 0.7808 0.04736 0.03539 -0.0687 0.2466 1.0012 2.250 0.8078 0.04965 0.03800 -0.0686 0.2410 1.0012 2.500 0.8347 0.05257 0.04130 -0.0686 0.2413 1.0012 2.750 0.8605 0.05592 0.04500 -0.0686 0.2444 1.0012 3.000 0.8846 0.05944 0.04881 -0.0685 0.2469 1.0012 3.250 0.9072 0.06316 0.05277 -0.0683 0.2487 1.0012 3.750 0.4900 0.10333 0.09618 -0.0754 0.9005 1.0012 4.000 0.4906 0.10708 0.09987 -0.0752 0.9080 1.0012 4.250 0.5256 0.11058 0.10331 -0.0797 0.8664 1.0012 4.750 0.6640 0.11486 0.10747 -0.0891 0.6910 1.0012 5.000 0.7207 0.11629 0.10885 -0.0874 0.6054 1.0012