XFOIL         Version 6.94
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) AIRFOI                
  
 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   0.4378   0.01180   0.00357  -0.0786  0.5319  0.0359
   0.500   0.4957   0.01166   0.00350  -0.0793  0.5251  0.0470
   1.000   0.5540   0.01140   0.00329  -0.0799  0.5189  0.0534
   1.500   0.6123   0.01117   0.00324  -0.0806  0.5126  0.1231
   2.000   0.6632   0.00931   0.00340  -0.0801  0.5058  1.0000
   2.500   0.7210   0.00944   0.00348  -0.0806  0.4992  1.0000
   3.000   0.7784   0.00959   0.00354  -0.0811  0.4900  1.0000
   3.500   0.8338   0.00940   0.00307  -0.0811  0.4241  1.0000
   4.000   0.8822   0.01114   0.00377  -0.0810  0.2319  1.0000
   4.500   0.9270   0.01352   0.00524  -0.0804  0.0534  1.0000
   5.000   0.9783   0.01451   0.00604  -0.0801  0.0058  1.0000
   5.500   1.0312   0.01517   0.00678  -0.0799  0.0058  1.0000
   6.000   1.0830   0.01591   0.00763  -0.0795  0.0065  1.0000
   6.500   1.1327   0.01687   0.00874  -0.0787  0.0075  1.0000
   7.000   1.1815   0.01784   0.00985  -0.0777  0.0090  1.0000
   7.500   1.2273   0.01903   0.01122  -0.0761  0.0109  1.0000
   8.000   1.2672   0.02066   0.01303  -0.0737  0.0131  1.0000
   8.500   1.2959   0.02292   0.01547  -0.0697  0.0150  1.0000
   9.000   1.2954   0.02640   0.01912  -0.0619  0.0168  1.0000
   9.500   1.3003   0.03010   0.02301  -0.0558  0.0197  1.0000
  10.000   1.2063   0.02312   0.01681  -0.0425  0.0213  1.0000