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MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 26 10.99% (mh26-il)
Reynolds number: 200,000
Max Cl/Cd: 57.81 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh26-il-200000-n5.txt
Download as CSV file: xf-mh26-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 26  10.99%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4744   0.12511   0.12150  -0.0320   1.0000   0.0158
 -11.250  -0.4766   0.12144   0.11786  -0.0322   1.0000   0.0158
 -11.000  -0.4790   0.11787   0.11432  -0.0325   1.0000   0.0158
 -10.750  -0.4818   0.11427   0.11074  -0.0328   1.0000   0.0158
  -9.750  -0.5085   0.09621   0.09280  -0.0328   1.0000   0.0087
  -9.500  -0.5127   0.09083   0.08745  -0.0360   0.9987   0.0085
  -9.250  -0.5170   0.08476   0.08141  -0.0407   0.9968   0.0083
  -9.000  -0.5234   0.07791   0.07455  -0.0476   0.9947   0.0082
  -8.750  -0.5366   0.07227   0.06885  -0.0510   0.9920   0.0081
  -8.500  -0.5508   0.06811   0.06459  -0.0513   0.9884   0.0079
  -8.250  -0.5619   0.06412   0.06048  -0.0505   0.9849   0.0078
  -8.000  -0.5698   0.05937   0.05556  -0.0495   0.9813   0.0077
  -7.750  -0.5739   0.05590   0.05192  -0.0473   0.9771   0.0075
  -7.500  -0.5769   0.05120   0.04697  -0.0452   0.9736   0.0073
  -7.250  -0.5708   0.04710   0.04256  -0.0440   0.9711   0.0070
  -7.000  -0.5736   0.04355   0.03871  -0.0398   0.9667   0.0069
  -6.750  -0.5699   0.03984   0.03463  -0.0364   0.9629   0.0067
  -6.500  -0.5599   0.03605   0.03039  -0.0338   0.9601   0.0064
  -6.250  -0.5447   0.03240   0.02619  -0.0317   0.9581   0.0063
  -6.000  -0.5346   0.02988   0.02325  -0.0283   0.9547   0.0062
  -5.750  -0.5196   0.02769   0.02065  -0.0256   0.9513   0.0061
  -5.500  -0.4980   0.02580   0.01835  -0.0243   0.9491   0.0062
  -5.250  -0.4729   0.02416   0.01642  -0.0237   0.9473   0.0062
  -5.000  -0.4458   0.02277   0.01480  -0.0235   0.9459   0.0064
  -4.750  -0.4178   0.02159   0.01344  -0.0236   0.9447   0.0068
  -4.500  -0.4009   0.02076   0.01250  -0.0214   0.9410   0.0071
  -4.250  -0.3812   0.01997   0.01159  -0.0197   0.9374   0.0077
  -4.000  -0.3562   0.01931   0.01081  -0.0192   0.9347   0.0087
  -3.750  -0.3289   0.01865   0.01011  -0.0194   0.9327   0.0121
  -3.500  -0.2990   0.01806   0.00936  -0.0198   0.9312   0.0162
  -3.250  -0.2859   0.01753   0.00878  -0.0167   0.9256   0.0239
  -3.000  -0.2662   0.01658   0.00832  -0.0154   0.9220   0.1066
  -2.750  -0.2440   0.01557   0.00799  -0.0149   0.9194   0.2566
  -2.500  -0.2252   0.01439   0.00770  -0.0136   0.9172   0.4687
  -2.250  -0.1959   0.01347   0.00824  -0.0131   0.9154   0.7936
  -2.000  -0.1291   0.01407   0.00877  -0.0205   0.9178   0.8759
  -1.750  -0.1061   0.01433   0.00894  -0.0191   0.9123   0.8997
  -1.500  -0.0680   0.01467   0.00916  -0.0209   0.9097   0.9171
  -1.250  -0.0138   0.01515   0.00951  -0.0260   0.9095   0.9317
  -1.000   0.0330   0.01533   0.00959  -0.0299   0.9080   0.9398
  -0.750   0.0759   0.01535   0.00952  -0.0331   0.9061   0.9448
  -0.500   0.1239   0.01531   0.00940  -0.0374   0.9049   0.9478
  -0.250   0.1456   0.01535   0.00940  -0.0361   0.8977   0.9563
   0.000   0.1937   0.01524   0.00926  -0.0405   0.8952   0.9589
   0.250   0.2401   0.01506   0.00906  -0.0445   0.8929   0.9614
   0.500   0.2862   0.01481   0.00879  -0.0484   0.8909   0.9635
   0.750   0.3050   0.01475   0.00874  -0.0465   0.8812   0.9700
   1.000   0.3493   0.01439   0.00839  -0.0500   0.8781   0.9709
   1.250   0.3785   0.01419   0.00823  -0.0505   0.8683   0.9740
   1.500   0.4103   0.01392   0.00798  -0.0513   0.8598   0.9768
   1.750   0.4425   0.01362   0.00771  -0.0522   0.8512   0.9794
   2.250   0.4985   0.01314   0.00733  -0.0523   0.8224   0.9847
   2.500   0.5358   0.01277   0.00701  -0.0542   0.8045   0.9856
   2.750   0.5845   0.01227   0.00650  -0.0582   0.7796   0.9847
   3.000   0.6345   0.01186   0.00597  -0.0624   0.7339   0.9832
   3.250   0.6710   0.01185   0.00572  -0.0640   0.6751   0.9835
   3.500   0.6979   0.01210   0.00570  -0.0639   0.6137   0.9851
   3.750   0.7203   0.01246   0.00580  -0.0629   0.5547   0.9876
   4.000   0.7400   0.01290   0.00602  -0.0616   0.4970   0.9904
   4.250   0.7584   0.01338   0.00627  -0.0600   0.4410   0.9932
   4.500   0.7789   0.01384   0.00652  -0.0590   0.3875   0.9954
   4.750   0.7999   0.01433   0.00679  -0.0581   0.3345   0.9976
   5.000   0.8217   0.01484   0.00712  -0.0575   0.2865   0.9998
   5.250   0.8350   0.01533   0.00747  -0.0549   0.2474   1.0000
   5.500   0.8469   0.01583   0.00783  -0.0521   0.2109   1.0000
   5.750   0.8585   0.01636   0.00827  -0.0492   0.1766   1.0000
   6.000   0.8698   0.01690   0.00868  -0.0464   0.1440   1.0000
   6.250   0.8807   0.01746   0.00912  -0.0434   0.1148   1.0000
   6.500   0.8919   0.01800   0.00958  -0.0405   0.0924   1.0000
   6.750   0.9026   0.01853   0.01007  -0.0375   0.0748   1.0000
   7.000   0.9126   0.01910   0.01060  -0.0343   0.0606   1.0000
   7.250   0.9217   0.01967   0.01116  -0.0309   0.0489   1.0000
   7.500   0.9291   0.02020   0.01171  -0.0272   0.0399   1.0000
   7.750   0.9348   0.02077   0.01232  -0.0231   0.0344   1.0000
   8.000   0.9408   0.02130   0.01295  -0.0192   0.0306   1.0000
   8.250   0.9448   0.02199   0.01369  -0.0149   0.0275   1.0000
   8.500   0.9477   0.02277   0.01456  -0.0104   0.0249   1.0000
   8.750   0.9543   0.02338   0.01536  -0.0067   0.0224   1.0000
   9.000   0.9609   0.02403   0.01609  -0.0032   0.0199   1.0000
   9.250   0.9630   0.02502   0.01714   0.0010   0.0176   1.0000
   9.500   0.9681   0.02590   0.01813   0.0047   0.0159   1.0000
   9.750   0.9749   0.02672   0.01909   0.0080   0.0138   1.0000
  10.000   0.9826   0.02741   0.01980   0.0108   0.0109   1.0000
  10.250   0.9830   0.02881   0.02133   0.0148   0.0098   1.0000
  10.500   0.9890   0.02986   0.02255   0.0179   0.0090   1.0000
  10.750   0.9931   0.03114   0.02400   0.0211   0.0078   1.0000
  11.000   0.9965   0.03241   0.02540   0.0242   0.0069   1.0000
  11.250   0.9985   0.03388   0.02701   0.0273   0.0066   1.0000
  11.500   0.9989   0.03554   0.02882   0.0304   0.0063   1.0000
  11.750   0.9933   0.03784   0.03129   0.0337   0.0059   1.0000
  12.000   0.9880   0.04033   0.03398   0.0368   0.0057   1.0000
  12.250   0.9840   0.04274   0.03670   0.0394   0.0055   1.0000
  12.500   0.9788   0.04525   0.03942   0.0417   0.0055   1.0000
  12.750   0.9702   0.04825   0.04268   0.0437   0.0053   1.0000
  13.000   0.9601   0.05149   0.04614   0.0452   0.0054   1.0000
  13.250   0.9465   0.05537   0.05027   0.0461   0.0052   1.0000
  13.500   0.9316   0.05971   0.05485   0.0461   0.0052   1.0000
  13.750   0.9164   0.06444   0.05980   0.0452   0.0052   1.0000
  14.000   0.9006   0.06977   0.06531   0.0434   0.0052   1.0000
  14.250   0.8815   0.07630   0.07205   0.0404   0.0052   1.0000
  14.500   0.8625   0.08351   0.07943   0.0365   0.0052   1.0000
  14.750   0.8476   0.09042   0.08647   0.0326   0.0054   1.0000
  15.000   0.8263   0.09946   0.09565   0.0273   0.0054   1.0000
  15.250   0.8059   0.10874   0.10499   0.0222   0.0055   1.0000
  15.500   0.7849   0.11867   0.11500   0.0170   0.0056   1.0000
  15.750   0.7598   0.13019   0.12657   0.0115   0.0057   1.0000
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