XFOIL         Version 6.94
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5)                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3741   0.01088   0.00295  -0.0557  0.5106  0.0332
   0.500   0.4300   0.01105   0.00292  -0.0558  0.4561  0.0379
   1.000   0.4857   0.01148   0.00315  -0.0561  0.4057  0.0507
   1.500   0.5417   0.01136   0.00289  -0.0562  0.3817  0.0545
   2.000   0.5979   0.01124   0.00277  -0.0564  0.3682  0.0626
   2.500   0.6543   0.01124   0.00278  -0.0566  0.3585  0.0837
   4.500   0.8722   0.01043   0.00364  -0.0565  0.2956  1.0000
   5.000   0.9270   0.01079   0.00384  -0.0566  0.2675  1.0000
   5.500   0.9814   0.01123   0.00414  -0.0566  0.2321  1.0000
   6.000   1.0183   0.01457   0.00622  -0.0553  0.0171  1.0000
   6.500   1.0691   0.01544   0.00711  -0.0548  0.0041  1.0000
   7.000   1.1199   0.01622   0.00798  -0.0542  0.0042  1.0000
   7.500   1.1691   0.01716   0.00907  -0.0535  0.0045  1.0000
   8.000   1.2167   0.01821   0.01028  -0.0525  0.0050  1.0000
   8.500   1.2621   0.01940   0.01165  -0.0513  0.0057  1.0000
   9.000   1.3032   0.02093   0.01337  -0.0495  0.0064  1.0000
   9.500   1.3405   0.02264   0.01529  -0.0473  0.0076  1.0000
  10.000   1.3698   0.02474   0.01759  -0.0443  0.0087  1.0000
  10.500   1.3720   0.02818   0.02127  -0.0387  0.0098  1.0000
  11.000   1.3782   0.03223   0.02560  -0.0360  0.0112  1.0000
  11.500   1.3641   0.03928   0.03284  -0.0349  0.0122  1.0000
  12.000   1.3650   0.04486   0.03866  -0.0328  0.0144  1.0000