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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.53 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh30-il-1000000.txt
Download as CSV file: xf-mh30-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 30  7.84%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4660   0.08313   0.08156  -0.0215   1.0000   0.0075
  -8.250  -0.4667   0.07880   0.07726  -0.0237   1.0000   0.0075
  -8.000  -0.4681   0.07463   0.07311  -0.0260   1.0000   0.0075
  -7.750  -0.4745   0.07025   0.06877  -0.0287   1.0000   0.0075
  -7.500  -0.4763   0.06456   0.06308  -0.0345   1.0000   0.0075
  -7.250  -0.4741   0.05849   0.05696  -0.0389   1.0000   0.0075
  -7.000  -0.4731   0.05335   0.05173  -0.0405   1.0000   0.0075
  -6.750  -0.4792   0.04942   0.04772  -0.0389   1.0000   0.0075
  -6.500  -0.4741   0.03313   0.03072  -0.0487   0.9937   0.0084
  -6.250  -0.4497   0.02940   0.02672  -0.0509   0.9896   0.0089
  -6.000  -0.4210   0.02655   0.02363  -0.0530   0.9864   0.0095
  -5.750  -0.3907   0.02408   0.02093  -0.0548   0.9838   0.0102
  -5.500  -0.3597   0.02169   0.01824  -0.0564   0.9811   0.0112
  -5.250  -0.3338   0.01974   0.01604  -0.0563   0.9749   0.0125
  -5.000  -0.3053   0.01818   0.01424  -0.0564   0.9701   0.0140
  -4.500  -0.2563   0.01220   0.00750  -0.0533   0.9567   0.0067
  -4.250  -0.2334   0.01051   0.00560  -0.0519   0.9494   0.0060
  -4.000  -0.2102   0.00937   0.00428  -0.0506   0.9425   0.0056
  -3.750  -0.1857   0.00862   0.00338  -0.0496   0.9351   0.0053
  -3.500  -0.1604   0.00812   0.00274  -0.0488   0.9285   0.0053
  -3.250  -0.1342   0.00777   0.00229  -0.0482   0.9211   0.0055
  -3.000  -0.1078   0.00755   0.00193  -0.0476   0.9146   0.0060
  -2.750  -0.0812   0.00721   0.00162  -0.0472   0.9071   0.0246
  -2.500  -0.0560   0.00669   0.00139  -0.0467   0.9002   0.1049
  -2.250  -0.0298   0.00637   0.00126  -0.0465   0.8923   0.1627
  -2.000  -0.0040   0.00600   0.00115  -0.0462   0.8848   0.2456
  -1.750   0.0207   0.00544   0.00105  -0.0458   0.8762   0.3882
  -1.500   0.0462   0.00506   0.00097  -0.0454   0.8665   0.4949
  -1.250   0.0721   0.00481   0.00092  -0.0450   0.8566   0.5722
  -1.000   0.0978   0.00458   0.00088  -0.0445   0.8465   0.6464
  -0.750   0.1234   0.00438   0.00085  -0.0439   0.8354   0.7151
  -0.500   0.1489   0.00422   0.00083  -0.0432   0.8234   0.7746
  -0.250   0.1740   0.00409   0.00082  -0.0424   0.8103   0.8278
   0.000   0.1987   0.00399   0.00082  -0.0415   0.7956   0.8779
   0.250   0.2240   0.00393   0.00082  -0.0406   0.7789   0.9255
   0.500   0.2580   0.00395   0.00082  -0.0417   0.7589   0.9612
   0.750   0.2967   0.00403   0.00081  -0.0440   0.7342   0.9814
   1.000   0.3351   0.00414   0.00080  -0.0463   0.7049   0.9925
   1.250   0.3729   0.00430   0.00081  -0.0486   0.6702   0.9999
   1.500   0.3975   0.00446   0.00084  -0.0479   0.6371   1.0000
   1.750   0.4218   0.00464   0.00088  -0.0472   0.6039   1.0000
   2.000   0.4464   0.00482   0.00094  -0.0466   0.5707   1.0000
   2.250   0.4710   0.00502   0.00101  -0.0459   0.5374   1.0000
   2.500   0.4958   0.00523   0.00109  -0.0453   0.5022   1.0000
   2.750   0.5205   0.00546   0.00121  -0.0447   0.4662   1.0000
   3.000   0.5454   0.00571   0.00132  -0.0442   0.4304   1.0000
   3.250   0.5703   0.00597   0.00144  -0.0437   0.3935   1.0000
   3.500   0.5951   0.00626   0.00158  -0.0432   0.3536   1.0000
   3.750   0.6202   0.00655   0.00173  -0.0427   0.3174   1.0000
   4.000   0.6453   0.00683   0.00192  -0.0423   0.2850   1.0000
   4.250   0.6701   0.00717   0.00211  -0.0418   0.2470   1.0000
   4.500   0.6946   0.00757   0.00232  -0.0413   0.2049   1.0000
   4.750   0.7192   0.00795   0.00255  -0.0409   0.1685   1.0000
   5.000   0.7430   0.00846   0.00283  -0.0404   0.1241   1.0000
   5.250   0.7673   0.00889   0.00311  -0.0399   0.0917   1.0000
   5.500   0.7921   0.00928   0.00339  -0.0394   0.0701   1.0000
   5.750   0.8168   0.00967   0.00373  -0.0390   0.0516   1.0000
   6.000   0.8412   0.01010   0.00408  -0.0385   0.0345   1.0000
   6.250   0.8652   0.01060   0.00448  -0.0380   0.0186   1.0000
   6.500   0.8880   0.01130   0.00509  -0.0372   0.0041   1.0000
   6.750   0.9121   0.01184   0.00573  -0.0364   0.0030   1.0000
   7.000   0.9360   0.01239   0.00637  -0.0357   0.0028   1.0000
   7.250   0.9593   0.01301   0.00710  -0.0350   0.0027   1.0000
   7.500   0.9814   0.01383   0.00805  -0.0339   0.0026   1.0000
   7.750   1.0024   0.01475   0.00912  -0.0328   0.0026   1.0000
   8.000   1.0213   0.01599   0.01054  -0.0313   0.0026   1.0000
   8.250   1.0389   0.01743   0.01216  -0.0296   0.0026   1.0000
   8.500   1.0548   0.01922   0.01422  -0.0277   0.0027   1.0000
   8.750   1.0691   0.02140   0.01665  -0.0257   0.0028   1.0000
   9.000   1.0809   0.02413   0.01968  -0.0234   0.0029   1.0000
   9.250   1.0870   0.02775   0.02368  -0.0206   0.0031   1.0000
   9.500   1.0892   0.03186   0.02809  -0.0176   0.0038   1.0000
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