XFOIL Version 6.94 Calculated polar for: wouaibair3 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 0.3203 0.03752 0.02347 -0.0715 0.3356 0.2913 -2.750 0.3664 0.03794 0.02387 -0.0749 0.3271 0.3115 -2.500 0.4195 0.03865 0.02461 -0.0799 0.3211 0.3407 -2.250 0.4755 0.03962 0.02570 -0.0859 0.3175 0.3720 -2.000 0.5267 0.04081 0.02703 -0.0909 0.3154 0.4037 -1.750 0.5662 0.04171 0.02824 -0.0934 0.3147 0.4317 -1.500 0.6011 0.04269 0.02949 -0.0950 0.3139 0.4618 -1.250 0.6314 0.04352 0.03071 -0.0954 0.3114 0.4928 -1.000 0.6613 0.04452 0.03207 -0.0958 0.3091 0.5260 -0.750 0.6911 0.04574 0.03375 -0.0961 0.3101 0.5680 -0.500 0.7226 0.04713 0.03544 -0.0968 0.3114 0.5906 -0.250 0.7530 0.04843 0.03708 -0.0973 0.3103 0.6081 0.000 0.7825 0.04989 0.03893 -0.0977 0.3094 0.6311 0.250 0.8114 0.05167 0.04117 -0.0980 0.3111 0.6649 0.500 0.8354 0.05305 0.04325 -0.0970 0.3110 0.7343 0.750 0.8596 0.05506 0.04565 -0.0962 0.3144 1.0024 1.000 0.8960 0.05772 0.04865 -0.0983 0.3354 1.0024 1.250 0.9309 0.06163 0.05280 -0.1007 0.3593 1.0024 1.500 1.0166 0.06182 0.05533 -0.1262 0.5828 1.0024 1.750 0.9025 0.07131 0.06553 -0.1191 0.6340 1.0024 2.750 0.4782 0.11408 0.10772 -0.0859 0.9805 0.6175 3.000 0.4949 0.11533 0.11004 -0.0872 0.9578 0.8983 3.250 0.5748 0.12194 0.11623 -0.1013 0.8912 1.0024 3.500 0.6491 0.12123 0.11517 -0.1067 0.7772 1.0024 3.750 0.8103 0.11551 0.10901 -0.1033 0.5545 1.0024 4.000 0.8627 0.11530 0.10863 -0.0968 0.4759 1.0024 4.250 0.9291 0.11628 0.10949 -0.0923 0.4247 1.0024 4.500 0.8854 0.12102 0.11415 -0.0885 0.3971 1.0024 4.750 0.8829 0.12493 0.11798 -0.0864 0.3720 1.0024 5.000 0.8856 0.12906 0.12203 -0.0848 0.3519 1.0024