XFOIL         Version 6.94
  
 Calculated polar for: bbl2                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.030 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.5232   0.03601   0.02494  -0.0404  0.3833  1.0019
  -2.750   0.5356   0.03573   0.02415  -0.0396  0.3705  1.0019
  -2.500   0.5606   0.03611   0.02393  -0.0405  0.3596  1.0019
  -2.250   0.5890   0.03683   0.02414  -0.0416  0.3523  1.0019
  -2.000   0.6184   0.03770   0.02462  -0.0427  0.3466  1.0019
  -1.750   0.6492   0.03866   0.02517  -0.0438  0.3420  1.0019
  -1.500   0.6815   0.03973   0.02588  -0.0451  0.3384  1.0019
  -1.250   0.7139   0.04094   0.02698  -0.0466  0.3356  1.0019
  -1.000   0.7461   0.04225   0.02822  -0.0479  0.3333  1.0019
  -0.750   0.7778   0.04369   0.02961  -0.0492  0.3315  1.0019
  -0.500   0.8086   0.04527   0.03119  -0.0504  0.3302  1.0019
  -0.250   0.8373   0.04705   0.03302  -0.0513  0.3293  1.0019
   0.000   0.8634   0.04909   0.03516  -0.0520  0.3289  1.0019
   0.250   0.8856   0.05151   0.03775  -0.0524  0.3290  1.0019
   0.500   0.9018   0.05451   0.04099  -0.0522  0.3298  1.0019
   0.750   0.9080   0.05849   0.04529  -0.0515  0.3313  1.0019
   1.000   0.8997   0.06382   0.05099  -0.0499  0.3337  1.0019
   1.250   0.8804   0.07019   0.05765  -0.0480  0.3366  1.0019
   1.500   0.8674   0.07609   0.06367  -0.0468  0.3391  1.0019