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MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 27 11.99% (mh27-il)
Reynolds number: 50,000
Max Cl/Cd: 30.68 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh27-il-50000-n5.txt
Download as CSV file: xf-mh27-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 27  11.99%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5087   0.10477   0.09794  -0.0397   1.0000   0.0342
  -9.750  -0.5190   0.10001   0.09325  -0.0411   1.0000   0.0334
  -9.500  -0.5340   0.09419   0.08749  -0.0436   1.0000   0.0326
  -9.250  -0.5556   0.08856   0.08188  -0.0456   1.0000   0.0314
  -9.000  -0.5866   0.08397   0.07724  -0.0445   1.0000   0.0306
  -8.500  -0.6359   0.07913   0.07223  -0.0362   1.0000   0.0297
  -8.250  -0.6510   0.07604   0.06907  -0.0325   1.0000   0.0296
  -8.000  -0.6624   0.07307   0.06594  -0.0290   1.0000   0.0294
  -7.750  -0.6729   0.07000   0.06275  -0.0253   1.0000   0.0292
  -7.500  -0.6839   0.06664   0.05920  -0.0212   1.0000   0.0292
  -7.250  -0.6892   0.06372   0.05610  -0.0177   1.0000   0.0289
  -7.000  -0.6947   0.06047   0.05259  -0.0138   1.0000   0.0289
  -6.750  -0.6969   0.05739   0.04922  -0.0100   1.0000   0.0288
  -6.500  -0.6970   0.05428   0.04577  -0.0062   1.0000   0.0288
  -6.250  -0.6939   0.05133   0.04247  -0.0027   1.0000   0.0287
  -6.000  -0.6883   0.04843   0.03913   0.0008   1.0000   0.0289
  -5.750  -0.6796   0.04573   0.03592   0.0041   1.0000   0.0293
  -5.500  -0.6679   0.04333   0.03311   0.0070   1.0000   0.0299
  -5.250  -0.6569   0.04090   0.03056   0.0090   1.0000   0.0328
  -5.000  -0.6404   0.03896   0.02830   0.0111   1.0000   0.0342
  -4.750  -0.6211   0.03700   0.02596   0.0130   1.0000   0.0368
  -4.500  -0.5981   0.03503   0.02361   0.0145   1.0000   0.0385
  -4.250  -0.5731   0.03336   0.02157   0.0157   1.0000   0.0406
  -4.000  -0.5503   0.03183   0.01994   0.0166   1.0000   0.0462
  -3.750  -0.5255   0.03059   0.01847   0.0176   1.0000   0.0553
  -3.500  -0.5016   0.02947   0.01725   0.0184   1.0000   0.0686
  -3.250  -0.4788   0.02813   0.01602   0.0193   1.0000   0.0982
  -3.000  -0.3222   0.02749   0.01882   0.0002   1.0000   0.9327
  -2.750  -0.1581   0.02897   0.01907  -0.0262   1.0000   1.0000
  -2.500  -0.1485   0.02875   0.01863  -0.0238   1.0000   1.0000
  -2.250  -0.1383   0.02858   0.01824  -0.0214   1.0000   1.0000
  -2.000  -0.1278   0.02846   0.01790  -0.0190   1.0000   1.0000
  -1.750  -0.1169   0.02838   0.01764  -0.0167   1.0000   1.0000
  -1.500  -0.1058   0.02834   0.01744  -0.0144   1.0000   1.0000
  -1.250  -0.0945   0.02834   0.01729  -0.0121   1.0000   1.0000
  -1.000  -0.0831   0.02837   0.01719  -0.0098   1.0000   1.0000
  -0.750  -0.0716   0.02844   0.01714  -0.0076   1.0000   1.0000
  -0.500  -0.0600   0.02855   0.01710  -0.0054   1.0000   1.0000
  -0.250  -0.0399   0.02873   0.01717  -0.0049   0.9976   1.0000
   0.000  -0.0036   0.02908   0.01740  -0.0077   0.9899   1.0000
   0.250   0.0326   0.02950   0.01772  -0.0105   0.9823   1.0000
   0.500   0.0667   0.02980   0.01794  -0.0128   0.9737   1.0000
   0.750   0.0997   0.03009   0.01818  -0.0148   0.9647   1.0000
   1.000   0.1353   0.03046   0.01851  -0.0173   0.9564   1.0000
   1.250   0.1677   0.03070   0.01874  -0.0190   0.9466   1.0000
   1.500   0.1980   0.03089   0.01894  -0.0203   0.9361   1.0000
   1.750   0.2301   0.03109   0.01916  -0.0219   0.9258   1.0000
   2.000   0.2650   0.03127   0.01940  -0.0239   0.9158   1.0000
   2.250   0.2988   0.03136   0.01956  -0.0256   0.9049   1.0000
   2.500   0.3279   0.03137   0.01964  -0.0264   0.8924   1.0000
   2.750   0.3572   0.03133   0.01968  -0.0270   0.8795   1.0000
   3.000   0.3867   0.03123   0.01973  -0.0276   0.8660   1.0000
   3.250   0.4164   0.03106   0.01969  -0.0281   0.8521   1.0000
   3.500   0.4469   0.03081   0.01958  -0.0286   0.8379   1.0000
   3.750   0.4675   0.03063   0.01952  -0.0272   0.8198   1.0000
   4.000   0.4956   0.03031   0.01942  -0.0270   0.8032   1.0000
   4.250   0.5272   0.02984   0.01914  -0.0272   0.7867   1.0000
   4.500   0.5610   0.02921   0.01872  -0.0275   0.7704   1.0000
   4.750   0.5836   0.02878   0.01849  -0.0259   0.7488   1.0000
   5.000   0.6190   0.02794   0.01794  -0.0261   0.7289   1.0000
   5.250   0.6477   0.02735   0.01756  -0.0251   0.7027   1.0000
   5.500   0.6827   0.02664   0.01705  -0.0251   0.6714   1.0000
   5.750   0.7231   0.02593   0.01650  -0.0259   0.6300   1.0000
   6.000   0.7627   0.02555   0.01619  -0.0268   0.5757   1.0000
   6.250   0.7888   0.02572   0.01625  -0.0256   0.5172   1.0000
   6.500   0.8042   0.02621   0.01657  -0.0228   0.4618   1.0000
   6.750   0.8125   0.02688   0.01706  -0.0191   0.4110   1.0000
   7.000   0.8183   0.02764   0.01764  -0.0150   0.3648   1.0000
   7.250   0.8222   0.02850   0.01834  -0.0109   0.3206   1.0000
   7.500   0.8260   0.02944   0.01912  -0.0069   0.2800   1.0000
   7.750   0.8291   0.03049   0.02001  -0.0029   0.2412   1.0000
   8.000   0.8339   0.03159   0.02100   0.0006   0.2059   1.0000
   8.250   0.8382   0.03282   0.02218   0.0041   0.1746   1.0000
   8.500   0.8434   0.03412   0.02338   0.0073   0.1472   1.0000
   8.750   0.8507   0.03552   0.02474   0.0102   0.1246   1.0000
   9.000   0.8581   0.03701   0.02617   0.0130   0.1066   1.0000
   9.250   0.8649   0.03846   0.02760   0.0158   0.0922   1.0000
   9.500   0.8782   0.04013   0.02939   0.0179   0.0807   1.0000
   9.750   0.8895   0.04181   0.03124   0.0201   0.0704   1.0000
  10.000   0.8999   0.04357   0.03310   0.0223   0.0629   1.0000
  10.250   0.9166   0.04571   0.03548   0.0238   0.0571   1.0000
  10.500   0.9328   0.04829   0.03819   0.0252   0.0527   1.0000
  10.750   0.9376   0.05061   0.04094   0.0280   0.0488   1.0000
  11.000   0.9346   0.05247   0.04295   0.0314   0.0450   1.0000
  11.250   0.9375   0.05488   0.04553   0.0337   0.0429   1.0000
  11.500   0.9345   0.05817   0.04914   0.0368   0.0415   1.0000
  11.750   0.9241   0.06127   0.05261   0.0401   0.0408   1.0000
  12.000   0.9102   0.06457   0.05623   0.0432   0.0403   1.0000
  12.250   0.8925   0.06817   0.06012   0.0459   0.0399   1.0000
  12.500   0.8724   0.07204   0.06425   0.0478   0.0395   1.0000
  12.750   0.8514   0.07634   0.06875   0.0487   0.0394   1.0000
  13.000   0.8302   0.08114   0.07373   0.0487   0.0397   1.0000
  13.250   0.8085   0.08645   0.07918   0.0475   0.0400   1.0000
  13.500   0.7863   0.09255   0.08540   0.0453   0.0405   1.0000
  13.750   0.7646   0.09934   0.09218   0.0422   0.0409   1.0000
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