XFOIL         Version 6.94
  
 Calculated polar for: MH32 (8.71%)                                    
  
 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   0.2637   0.00691   0.00182  -0.0550  0.7500  0.8788
   0.500   0.3419   0.00709   0.00150  -0.0590  0.6544  0.9896
   1.000   0.3791   0.00902   0.00171  -0.0560  0.3186  1.0000
   1.500   0.4230   0.01041   0.00234  -0.0541  0.1292  1.0000
   2.000   0.4696   0.01162   0.00314  -0.0526  0.0161  1.0000
   2.500   0.5217   0.01197   0.00341  -0.0521  0.0148  1.0000
   3.000   0.5740   0.01229   0.00359  -0.0516  0.0138  1.0000
   3.500   0.6264   0.01264   0.00380  -0.0512  0.0130  1.0000
   4.000   0.6785   0.01301   0.00412  -0.0508  0.0117  1.0000
   4.500   0.7305   0.01344   0.00446  -0.0503  0.0107  1.0000
   5.000   0.7820   0.01392   0.00489  -0.0498  0.0100  1.0000
   5.500   0.8335   0.01440   0.00539  -0.0492  0.0108  1.0000
   6.000   0.8844   0.01497   0.00611  -0.0485  0.0138  1.0000
   6.500   0.9341   0.01567   0.00707  -0.0475  0.0124  1.0000
   7.000   0.9822   0.01657   0.00816  -0.0464  0.0076  1.0000
   7.500   1.0240   0.01824   0.00991  -0.0444  0.0033  1.0000
   8.000   1.0652   0.01990   0.01187  -0.0424  0.0032  1.0000
   8.500   1.1017   0.02199   0.01427  -0.0398  0.0032  1.0000
   9.000   1.1323   0.02446   0.01713  -0.0367  0.0031  1.0000
   9.500   1.1558   0.02736   0.02034  -0.0328  0.0031  1.0000
  10.000   1.1709   0.03033   0.02359  -0.0280  0.0030  1.0000
  10.500   1.1763   0.03406   0.02763  -0.0229  0.0030  1.0000
  11.000   1.1788   0.03824   0.03212  -0.0190  0.0030  1.0000
  11.500   1.1749   0.04354   0.03778  -0.0163  0.0029  1.0000
  12.000   1.1664   0.04990   0.04448  -0.0154  0.0029  1.0000
  12.500   1.1513   0.05805   0.05308  -0.0168  0.0029  1.0000
  13.000   1.1329   0.06792   0.06333  -0.0208  0.0029  1.0000
  13.500   1.1067   0.08071   0.07654  -0.0278  0.0029  1.0000
  14.000   1.0808   0.09520   0.09139  -0.0364  0.0029  1.0000
  14.500   1.0504   0.11245   0.10901  -0.0467  0.0029  1.0000
  15.000   1.0212   0.13089   0.12773  -0.0572  0.0030  1.0000
  15.500   0.9927   0.15071   0.14778  -0.0677  0.0031  1.0000
  16.000   0.9696   0.17067   0.16788  -0.0777  0.0032  1.0000
  16.500   0.9572   0.18849   0.18574  -0.0861  0.0032  1.0000
  17.000   0.9588   0.20150   0.19872  -0.0925  0.0033  1.0000