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MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 62 9.3% (mh62-il)
Reynolds number: 50,000
Max Cl/Cd: 33.12 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh62-il-50000-n5.txt
Download as CSV file: xf-mh62-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 62  9.3%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5483   0.09492   0.08854  -0.0001   1.0000   0.0350
  -8.750  -0.5492   0.08993   0.08362  -0.0033   1.0000   0.0347
  -8.500  -0.5513   0.08462   0.07839  -0.0070   1.0000   0.0343
  -8.250  -0.5548   0.07885   0.07269  -0.0116   1.0000   0.0334
  -8.000  -0.5616   0.07244   0.06631  -0.0170   1.0000   0.0326
  -7.750  -0.5669   0.06652   0.06031  -0.0211   1.0000   0.0318
  -7.500  -0.5694   0.06104   0.05466  -0.0242   1.0000   0.0317
  -7.250  -0.5676   0.05598   0.04934  -0.0263   1.0000   0.0316
  -7.000  -0.5613   0.05143   0.04446  -0.0276   1.0000   0.0323
  -6.750  -0.5512   0.04718   0.03981  -0.0284   1.0000   0.0331
  -6.500  -0.5378   0.04324   0.03539  -0.0286   1.0000   0.0341
  -6.250  -0.5213   0.03958   0.03122  -0.0284   1.0000   0.0350
  -6.000  -0.5020   0.03630   0.02741  -0.0279   1.0000   0.0358
  -5.750  -0.4806   0.03339   0.02400  -0.0272   1.0000   0.0369
  -5.500  -0.4575   0.03097   0.02110  -0.0263   1.0000   0.0384
  -5.250  -0.4372   0.02883   0.01890  -0.0256   1.0000   0.0429
  -5.000  -0.4151   0.02720   0.01699  -0.0246   1.0000   0.0493
  -4.750  -0.3955   0.02543   0.01518  -0.0232   1.0000   0.0551
  -4.500  -0.3773   0.02405   0.01375  -0.0218   1.0000   0.0681
  -4.250  -0.3602   0.02266   0.01234  -0.0201   1.0000   0.0881
  -4.000  -0.3429   0.02105   0.01108  -0.0188   1.0000   0.1368
  -3.750  -0.3274   0.01983   0.01038  -0.0175   1.0000   0.2408
  -3.500  -0.3134   0.01915   0.01007  -0.0157   1.0000   0.3347
  -3.250  -0.2991   0.01865   0.00982  -0.0137   1.0000   0.4125
  -3.000  -0.2659   0.01814   0.00943  -0.0148   0.9874   0.5012
  -2.750  -0.2316   0.01769   0.00916  -0.0158   0.9761   0.5851
  -2.500  -0.1961   0.01731   0.00896  -0.0166   0.9660   0.6757
  -2.250  -0.1533   0.01701   0.00882  -0.0182   0.9577   0.7820
  -2.000  -0.0850   0.01686   0.00849  -0.0247   0.9536   0.8962
  -1.750  -0.0082   0.01674   0.00800  -0.0340   0.9486   0.9747
  -1.500   0.0434   0.01672   0.00763  -0.0393   0.9378   1.0000
  -1.250   0.0787   0.01681   0.00745  -0.0413   0.9225   1.0000
  -1.000   0.1108   0.01693   0.00735  -0.0425   0.9070   1.0000
  -0.750   0.1399   0.01708   0.00732  -0.0429   0.8915   1.0000
  -0.500   0.1666   0.01725   0.00730  -0.0428   0.8762   1.0000
  -0.250   0.1915   0.01743   0.00734  -0.0421   0.8610   1.0000
   0.000   0.2151   0.01762   0.00740  -0.0411   0.8460   1.0000
   0.250   0.2374   0.01783   0.00749  -0.0400   0.8304   1.0000
   0.500   0.2595   0.01803   0.00760  -0.0387   0.8149   1.0000
   0.750   0.2816   0.01823   0.00771  -0.0373   0.7994   1.0000
   1.000   0.3039   0.01842   0.00784  -0.0360   0.7841   1.0000
   1.250   0.3262   0.01860   0.00796  -0.0346   0.7686   1.0000
   1.500   0.3486   0.01877   0.00810  -0.0332   0.7532   1.0000
   1.750   0.3713   0.01893   0.00822  -0.0318   0.7376   1.0000
   2.000   0.3940   0.01907   0.00833  -0.0304   0.7220   1.0000
   2.250   0.4169   0.01923   0.00847  -0.0290   0.7053   1.0000
   2.500   0.4399   0.01940   0.00865  -0.0278   0.6875   1.0000
   2.750   0.4631   0.01954   0.00883  -0.0264   0.6700   1.0000
   3.000   0.4866   0.01965   0.00894  -0.0251   0.6527   1.0000
   3.250   0.5102   0.01982   0.00914  -0.0239   0.6332   1.0000
   3.500   0.5339   0.01996   0.00930  -0.0227   0.6137   1.0000
   3.750   0.5576   0.02011   0.00951  -0.0214   0.5938   1.0000
   4.000   0.5814   0.02029   0.00973  -0.0202   0.5723   1.0000
   4.250   0.6051   0.02049   0.00995  -0.0191   0.5504   1.0000
   4.500   0.6289   0.02070   0.01017  -0.0178   0.5282   1.0000
   4.750   0.6525   0.02100   0.01056  -0.0168   0.5040   1.0000
   5.000   0.6760   0.02132   0.01090  -0.0157   0.4798   1.0000
   5.250   0.6994   0.02169   0.01128  -0.0146   0.4554   1.0000
   5.500   0.7225   0.02212   0.01172  -0.0136   0.4306   1.0000
   5.750   0.7453   0.02264   0.01228  -0.0126   0.4047   1.0000
   6.000   0.7678   0.02322   0.01296  -0.0117   0.3790   1.0000
   6.250   0.7899   0.02385   0.01364  -0.0108   0.3535   1.0000
   6.500   0.8117   0.02456   0.01438  -0.0099   0.3286   1.0000
   6.750   0.8329   0.02532   0.01516  -0.0090   0.3041   1.0000
   7.000   0.8536   0.02616   0.01608  -0.0081   0.2799   1.0000
   7.250   0.8737   0.02709   0.01709  -0.0072   0.2559   1.0000
   7.500   0.8931   0.02809   0.01822  -0.0063   0.2334   1.0000
   7.750   0.9118   0.02917   0.01937  -0.0053   0.2117   1.0000
   8.000   0.9294   0.03036   0.02065  -0.0044   0.1903   1.0000
   8.250   0.9458   0.03163   0.02197  -0.0033   0.1704   1.0000
   8.500   0.9611   0.03306   0.02351  -0.0023   0.1509   1.0000
   8.750   0.9748   0.03460   0.02514  -0.0012   0.1328   1.0000
   9.000   0.9867   0.03627   0.02684  -0.0001   0.1168   1.0000
   9.250   0.9972   0.03812   0.02872   0.0011   0.1026   1.0000
   9.500   1.0054   0.04007   0.03077   0.0023   0.0897   1.0000
   9.750   1.0144   0.04236   0.03329   0.0036   0.0794   1.0000
  10.000   1.0193   0.04474   0.03595   0.0048   0.0704   1.0000
  10.250   1.0212   0.04693   0.03806   0.0061   0.0640   1.0000
  10.500   1.0246   0.05006   0.04163   0.0074   0.0590   1.0000
  10.750   1.0241   0.05278   0.04448   0.0082   0.0549   1.0000
  11.000   1.0220   0.05578   0.04752   0.0086   0.0514   1.0000
  11.250   1.0140   0.05982   0.05194   0.0084   0.0489   1.0000
  11.500   1.0043   0.06410   0.05650   0.0074   0.0467   1.0000
  11.750   0.9939   0.06878   0.06140   0.0059   0.0455   1.0000
  12.000   0.9805   0.07426   0.06709   0.0036   0.0448   1.0000
  12.250   0.9638   0.08068   0.07371   0.0002   0.0447   1.0000
  12.500   0.9414   0.08878   0.08202  -0.0048   0.0454   1.0000
  12.750   0.9121   0.09942   0.09283  -0.0115   0.0474   1.0000
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