XFOIL         Version 6.94
  
 Calculated polar for: D.G.A. 1182                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.0648   0.01349   0.00399  -0.0116  0.1805  0.4194
   0.500   0.1198   0.01356   0.00399  -0.0116  0.1789  0.4225
   1.000   0.1743   0.01385   0.00419  -0.0116  0.1761  0.4257
   1.500   0.2272   0.01471   0.00483  -0.0115  0.1717  0.4275
   2.000   0.2805   0.01559   0.00563  -0.0114  0.1615  0.4290
   2.500   0.3337   0.01673   0.00679  -0.0113  0.1447  0.4311
   3.000   0.3877   0.01712   0.00738  -0.0113  0.1275  0.4333
   4.000   0.4993   0.01600   0.00688  -0.0112  0.0948  0.4367
   4.500   0.5579   0.01531   0.00626  -0.0114  0.0751  0.4383
   5.000   0.6093   0.01640   0.00753  -0.0108  0.0637  0.4408
   5.500   0.6589   0.01803   0.00934  -0.0099  0.0586  0.4431
   6.000   0.7101   0.01935   0.01099  -0.0093  0.0542  0.4457
   6.500   0.7618   0.01979   0.01169  -0.0091  0.0454  0.4496
   7.000   0.8127   0.02029   0.01247  -0.0088  0.0294  0.4524
   7.500   0.8608   0.02244   0.01499  -0.0077  0.0178  0.4550
   8.000   0.8960   0.02910   0.02256  -0.0053  0.0141  0.4578
   8.500   0.9199   0.03924   0.03399  -0.0025  0.0131  0.4607
   9.000   0.8912   0.05834   0.05424   0.0000  0.0137  0.4607