XFOIL         Version 6.94
  
 Calculated polar for: BL BAP 04                                       
  
 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  -0.0184   0.04527   0.03661  -0.0709  0.9254  0.2350
  -2.750   0.0161   0.04284   0.03415  -0.0727  0.9160  0.2289
  -2.500   0.0478   0.04089   0.03212  -0.0737  0.9031  0.2229
  -2.250   0.0743   0.03944   0.03055  -0.0737  0.8832  0.2175
  -2.000   0.0651   0.03921   0.03042  -0.0672  0.8233  0.2153
  -1.750   0.1146   0.03770   0.02852  -0.0713  0.7694  0.2103
  -1.500   0.1848   0.03553   0.02590  -0.0785  0.7531  0.2076
  -1.250   0.2589   0.03331   0.02320  -0.0863  0.7424  0.2085
  -1.000   0.3423   0.03120   0.02064  -0.0962  0.7289  0.2162
  -0.750   0.4114   0.03012   0.01913  -0.1039  0.7165  0.2309
  -0.500   0.4640   0.02937   0.01825  -0.1087  0.7065  0.2492
  -0.250   0.5099   0.02890   0.01785  -0.1125  0.6974  0.2831