XFOIL         Version 6.94
  
 Calculated polar for: MH 64  8.59%                                    
  
 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   0.1264   0.00579   0.00163  -0.0169  0.7207  0.9942
   0.500   0.1855   0.00579   0.00151  -0.0174  0.6982  1.0000
   1.000   0.2385   0.00591   0.00145  -0.0166  0.6700  1.0000
   1.500   0.2920   0.00601   0.00142  -0.0159  0.6377  1.0000
   2.000   0.3460   0.00616   0.00146  -0.0153  0.6018  1.0000
   2.500   0.3999   0.00640   0.00154  -0.0147  0.5582  1.0000
   3.000   0.4537   0.00671   0.00168  -0.0142  0.5059  1.0000
   3.500   0.5077   0.00710   0.00189  -0.0138  0.4546  1.0000
   4.000   0.5615   0.00756   0.00220  -0.0134  0.4003  1.0000
   4.500   0.6152   0.00808   0.00257  -0.0131  0.3476  1.0000
   5.000   0.6683   0.00870   0.00303  -0.0128  0.2925  1.0000
   5.500   0.7211   0.00940   0.00358  -0.0125  0.2351  1.0000
   6.000   0.7734   0.01018   0.00427  -0.0121  0.1840  1.0000
   6.500   0.8241   0.01123   0.00507  -0.0117  0.1257  1.0000
   7.000   0.8748   0.01222   0.00595  -0.0113  0.0866  1.0000
   7.500   0.9228   0.01370   0.00722  -0.0106  0.0413  1.0000
   8.500   1.0101   0.01801   0.01173  -0.0079  0.0091  1.0000
  10.000   1.0615   0.03587   0.03158   0.0022  0.0060  1.0000
  10.500   1.0521   0.04143   0.03760   0.0057  0.0059  1.0000
  11.000   1.0270   0.04893   0.04552   0.0057  0.0059  1.0000
  12.000   0.9781   0.06952   0.06676  -0.0061  0.0056  1.0000