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 = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.2936 0.03875 0.02466 -0.0658 0.3651 0.3120 -2.750 0.3412 0.03923 0.02499 -0.0694 0.3560 0.3311 -2.500 0.3877 0.03981 0.02558 -0.0730 0.3463 0.3568 -2.000 0.4964 0.04148 0.02754 -0.0842 0.3363 0.4238 -1.750 0.5421 0.04215 0.02859 -0.0879 0.3346 0.4555 -1.500 0.5843 0.04298 0.02977 -0.0909 0.3339 0.4907 -1.250 0.6215 0.04385 0.03103 -0.0927 0.3322 0.5277 -1.000 0.6538 0.04474 0.03239 -0.0933 0.3284 0.5693 -0.750 0.6832 0.04581 0.03393 -0.0933 0.3268 0.6124 -0.500 0.7159 0.04705 0.03548 -0.0943 0.3285 0.6335 -0.250 0.7479 0.04839 0.03715 -0.0951 0.3292 0.6572 0.000 0.7770 0.04968 0.03887 -0.0954 0.3269 0.6900 0.250 0.8027 0.05079 0.04064 -0.0948 0.3281 0.7534 0.500 0.8297 0.05189 0.04219 -0.0945 0.3300 1.0024 0.750 0.8625 0.05461 0.04488 -0.0963 0.3306 1.0024 1.000 0.8948 0.05823 0.04844 -0.0978 0.3382 1.0024 1.250 0.9269 0.06134 0.05194 -0.0996 0.3584 1.0024 1.500 0.9607 0.06362 0.05500 -0.1029 0.3983 1.0024 1.750 1.0054 0.06600 0.05872 -0.1162 0.5213 1.0024 2.000 0.9537 0.07392 0.06737 -0.1200 0.6072 1.0024 2.250 0.7577 0.09135 0.08504 -0.1089 0.6744 1.0024 2.500 0.5167 0.10827 0.10270 -0.0909 0.9127 1.0024 2.750 0.4800 0.11065 0.10502 -0.0839 0.9557 1.0024 3.250 0.4757 0.11743 0.11141 -0.0817 0.9852 1.0024 3.500 0.5141 0.12209 0.11582 -0.0892 0.9560 1.0024 3.750 0.5598 0.12612 0.11964 -0.0967 0.9020 1.0024 4.000 0.6160 0.12937 0.12265 -0.1032 0.8249 1.0024 4.250 0.7163 0.12973 0.12276 -0.1075 0.6801 1.0024 4.500 0.8001 0.13050 0.12330 -0.1038 0.5552 1.0024 4.750 0.8608 0.13312 0.12580 -0.1005 0.4924 1.0024 5.000 0.8545 0.13520 0.12784 -0.0962 0.4519 1.0024