XFOIL         Version 6.94
  
 Calculated polar for: MH 30                                           
  
 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   0.2724   0.00692   0.00260  -0.0605  0.9133  1.0000
   0.500   0.3160   0.00681   0.00237  -0.0573  0.8873  1.0000
   1.000   0.3605   0.00678   0.00224  -0.0543  0.8579  1.0000
   1.500   0.4069   0.00678   0.00215  -0.0517  0.8240  1.0000
   2.000   0.4547   0.00685   0.00211  -0.0494  0.7806  1.0000
   2.500   0.5031   0.00702   0.00213  -0.0473  0.7259  1.0000
   3.000   0.5512   0.00739   0.00227  -0.0452  0.6551  1.0000
   3.500   0.5988   0.00794   0.00253  -0.0433  0.5744  1.0000
   4.000   0.6460   0.00863   0.00290  -0.0416  0.4858  1.0000
   4.500   0.6927   0.00946   0.00346  -0.0399  0.3917  1.0000
   5.000   0.7392   0.01043   0.00410  -0.0384  0.2980  1.0000
   5.500   0.7848   0.01159   0.00488  -0.0370  0.2018  1.0000
   6.000   0.8301   0.01290   0.00581  -0.0356  0.1154  1.0000
   6.500   0.8715   0.01486   0.00732  -0.0336  0.0337  1.0000
   7.000   0.9055   0.01824   0.01100  -0.0296  0.0158  1.0000
   7.500   0.9437   0.02130   0.01437  -0.0265  0.0144  1.0000
   8.000   0.9822   0.02564   0.01919  -0.0234  0.0140  1.0000
   8.500   1.0196   0.02830   0.02214  -0.0212  0.0117  1.0000
   9.000   1.0452   0.03352   0.02787  -0.0178  0.0108  1.0000
   9.500   1.0548   0.04026   0.03532  -0.0131  0.0106  1.0000
  10.000   1.0484   0.04671   0.04244  -0.0075  0.0109  1.0000
  10.500   0.9965   0.05606   0.05254  -0.0009  0.0121  1.0000