XFOIL         Version 6.94
  
 Calculated polar for: RG-12                                           
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.2241   0.00756   0.00306  -0.0353  0.8582  0.9336
   1.000   0.2856   0.00756   0.00295  -0.0355  0.8231  0.9512
   1.500   0.3519   0.00764   0.00291  -0.0372  0.7812  0.9650
   2.000   0.4264   0.00778   0.00288  -0.0410  0.7328  0.9730
   2.500   0.4956   0.00798   0.00292  -0.0438  0.6773  0.9821
   3.000   0.5646   0.00826   0.00299  -0.0468  0.6156  0.9917
   3.500   0.6278   0.00861   0.00313  -0.0489  0.5473  1.0000
   4.000   0.6558   0.00900   0.00336  -0.0438  0.4870  1.0000
   4.500   0.6901   0.00953   0.00369  -0.0399  0.4244  1.0000
   5.000   0.7331   0.01022   0.00415  -0.0377  0.3546  1.0000
   5.500   0.7772   0.01111   0.00479  -0.0359  0.2748  1.0000
   6.000   0.8203   0.01227   0.00557  -0.0341  0.1863  1.0000
   6.500   0.8635   0.01357   0.00658  -0.0323  0.1148  1.0000
   7.000   0.9043   0.01521   0.00798  -0.0301  0.0603  1.0000
   9.000   1.0405   0.02584   0.01933  -0.0169  0.0146  1.0000
   9.500   1.0704   0.02992   0.02390  -0.0134  0.0134  1.0000
  10.000   1.0887   0.03537   0.02997  -0.0090  0.0132  1.0000
  10.500   1.0833   0.04184   0.03713  -0.0026  0.0135  1.0000
  11.000   1.0551   0.04854   0.04440   0.0042  0.0139  1.0000
  11.500   1.0172   0.05663   0.05296   0.0066  0.0143  1.0000
  12.000   0.9757   0.06726   0.06397   0.0031  0.0146  1.0000
  12.500   0.9353   0.08119   0.07821  -0.0060  0.0147  1.0000
  13.000   0.8875   0.10148   0.09870  -0.0205  0.0151  1.0000