XFOIL Version 6.94 Calculated polar for: bbl1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0999 0.05986 0.04695 -0.0268 0.9984 0.4576 -2.750 0.1152 0.06161 0.04876 -0.0270 0.9984 0.4784 -2.500 0.1301 0.06341 0.05060 -0.0272 0.9984 0.4943 -2.250 0.1450 0.06521 0.05254 -0.0274 0.9984 0.5152 -2.000 0.1596 0.06703 0.05456 -0.0275 0.9984 0.5424 -1.750 0.1739 0.06890 0.05662 -0.0276 0.9984 0.5687 -1.500 0.2028 0.07087 0.05895 -0.0302 0.9916 0.6138 -1.250 0.2377 0.07253 0.06109 -0.0333 0.9747 0.6749 -1.000 0.2604 0.07395 0.06307 -0.0333 0.9623 0.7462 -0.750 0.2790 0.07502 0.06467 -0.0320 0.9501 0.8588 -0.500 0.2741 0.07571 0.06547 -0.0297 0.9483 1.0016 -0.250 0.2891 0.07792 0.06749 -0.0312 0.9443 1.0016 0.000 0.3273 0.08084 0.07008 -0.0366 0.9285 1.0016 0.250 0.3398 0.08321 0.07226 -0.0378 0.9251 1.0016 0.500 0.3555 0.08637 0.07520 -0.0399 0.9291 1.0016