XFOIL Version 6.94 Calculated polar for: fauvel bl2 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 0.0851 0.03202 0.02247 -0.0528 0.8871 0.3480 -2.750 0.1100 0.03184 0.02221 -0.0503 0.8602 0.3650 -2.500 0.1310 0.03170 0.02212 -0.0469 0.8332 0.3860 -2.250 0.1491 0.03160 0.02209 -0.0424 0.8042 0.4127 -2.000 0.1671 0.03107 0.02192 -0.0382 0.7696 0.4596 -1.750 0.1726 0.02897 0.02160 -0.0299 0.7385 0.7074 -1.500 0.1995 0.02845 0.02035 -0.0253 0.6905 1.0005 -1.250 0.2183 0.02857 0.02001 -0.0208 0.6330 1.0005 -1.000 0.2408 0.02839 0.01939 -0.0174 0.5670 1.0005 -0.750 0.2665 0.02812 0.01863 -0.0151 0.5152 1.0005 -0.500 0.2943 0.02816 0.01816 -0.0139 0.4774 1.0005 -0.250 0.3226 0.02840 0.01789 -0.0130 0.4502 1.0005 0.000 0.3522 0.02891 0.01800 -0.0127 0.4291 1.0005 0.250 0.3827 0.02964 0.01843 -0.0129 0.4136 1.0005 0.500 0.4117 0.03030 0.01869 -0.0125 0.4017 1.0005 0.750 0.4431 0.03129 0.01959 -0.0132 0.3894 1.0005 1.000 0.4720 0.03211 0.02007 -0.0130 0.3803 1.0005 1.250 0.5035 0.03335 0.02134 -0.0140 0.3715 1.0005 1.500 0.5337 0.03451 0.02237 -0.0144 0.3655 1.0005 1.750 0.5630 0.03573 0.02335 -0.0145 0.3609 1.0005 2.000 0.5953 0.03761 0.02543 -0.0164 0.3562 1.0005 2.250 0.6263 0.03946 0.02738 -0.0179 0.3512 1.0005 2.500 0.6560 0.04113 0.02902 -0.0188 0.3465 1.0005 2.750 0.6847 0.04275 0.03055 -0.0193 0.3427 1.0005 3.000 0.7139 0.04511 0.03295 -0.0208 0.3408 1.0005 3.250 0.7431 0.04852 0.03665 -0.0238 0.3401 1.0005 3.500 0.7700 0.05253 0.04093 -0.0273 0.3399 1.0005 3.750 0.7931 0.05750 0.04619 -0.0316 0.3401 1.0005 4.000 0.8110 0.06321 0.05214 -0.0360 0.3408 1.0005