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MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 44 9.66% (mh44-il)
Reynolds number: 50,000
Max Cl/Cd: 32.78 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh44-il-50000-n5.txt
Download as CSV file: xf-mh44-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 44  9.66%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4426   0.14593   0.13950   0.0107   1.0000   0.0972
 -12.250  -0.4404   0.14284   0.13641   0.0093   1.0000   0.0969
 -12.000  -0.5695   0.14298   0.13590   0.0092   1.0000   0.0501
 -11.750  -0.5559   0.13866   0.13156   0.0099   1.0000   0.0489
 -11.500  -0.5479   0.13456   0.12747   0.0091   1.0000   0.0475
 -11.250  -0.5424   0.13046   0.12340   0.0076   1.0000   0.0460
 -11.000  -0.5390   0.12615   0.11913   0.0058   1.0000   0.0451
 -10.750  -0.5366   0.12163   0.11466   0.0037   1.0000   0.0435
 -10.250  -0.5473   0.10910   0.10227  -0.0055   1.0000   0.0382
 -10.000  -0.5437   0.10488   0.09809  -0.0069   1.0000   0.0379
  -9.750  -0.5414   0.10055   0.09380  -0.0086   1.0000   0.0375
  -9.500  -0.5411   0.09588   0.08919  -0.0108   1.0000   0.0372
  -9.250  -0.5416   0.09108   0.08446  -0.0133   1.0000   0.0368
  -9.000  -0.5444   0.08574   0.07918  -0.0166   1.0000   0.0364
  -8.750  -0.5480   0.08016   0.07365  -0.0206   1.0000   0.0358
  -8.500  -0.5569   0.07425   0.06778  -0.0252   1.0000   0.0353
  -8.250  -0.5674   0.06939   0.06289  -0.0276   1.0000   0.0349
  -8.000  -0.5754   0.06444   0.05783  -0.0295   1.0000   0.0344
  -7.750  -0.5797   0.05979   0.05300  -0.0307   1.0000   0.0340
  -7.500  -0.5808   0.05529   0.04823  -0.0311   1.0000   0.0338
  -7.250  -0.5777   0.05110   0.04371  -0.0310   1.0000   0.0336
  -7.000  -0.5715   0.04706   0.03926  -0.0304   1.0000   0.0336
  -6.750  -0.5616   0.04342   0.03518  -0.0294   1.0000   0.0336
  -6.500  -0.5488   0.04012   0.03143  -0.0282   1.0000   0.0340
  -6.250  -0.5333   0.03717   0.02803  -0.0269   1.0000   0.0346
  -6.000  -0.5158   0.03454   0.02492  -0.0254   1.0000   0.0356
  -5.750  -0.4967   0.03239   0.02229  -0.0238   1.0000   0.0378
  -5.500  -0.4794   0.03033   0.02016  -0.0224   1.0000   0.0409
  -5.250  -0.4613   0.02870   0.01838  -0.0207   1.0000   0.0450
  -5.000  -0.4426   0.02710   0.01652  -0.0187   1.0000   0.0487
  -4.750  -0.4267   0.02566   0.01507  -0.0168   1.0000   0.0556
  -4.500  -0.4103   0.02434   0.01364  -0.0147   1.0000   0.0658
  -4.250  -0.3936   0.02300   0.01233  -0.0129   1.0000   0.0867
  -4.000  -0.3756   0.02122   0.01103  -0.0117   1.0000   0.1516
  -3.750  -0.3604   0.02007   0.01045  -0.0101   1.0000   0.2721
  -3.500  -0.3475   0.01942   0.01021  -0.0078   1.0000   0.3717
  -3.250  -0.3336   0.01890   0.00997  -0.0053   1.0000   0.4501
  -3.000  -0.3177   0.01844   0.00967  -0.0031   1.0000   0.5148
  -2.750  -0.3009   0.01801   0.00940  -0.0009   1.0000   0.5820
  -2.500  -0.2754   0.01760   0.00918   0.0000   0.9959   0.6693
  -2.250  -0.2254   0.01729   0.00911  -0.0030   0.9893   0.8011
  -2.000  -0.1354   0.01730   0.00885  -0.0140   0.9898   0.9385
  -1.750  -0.0665   0.01742   0.00851  -0.0226   0.9858   1.0000
  -1.500  -0.0220   0.01750   0.00828  -0.0268   0.9719   1.0000
  -1.250   0.0233   0.01758   0.00807  -0.0309   0.9585   1.0000
  -1.000   0.0683   0.01764   0.00792  -0.0348   0.9451   1.0000
  -0.750   0.1103   0.01770   0.00781  -0.0379   0.9307   1.0000
  -0.500   0.1496   0.01777   0.00771  -0.0403   0.9157   1.0000
  -0.250   0.1859   0.01784   0.00766  -0.0420   0.9002   1.0000
   0.000   0.2154   0.01795   0.00768  -0.0423   0.8824   1.0000
   0.250   0.2435   0.01807   0.00770  -0.0422   0.8648   1.0000
   0.500   0.2702   0.01819   0.00774  -0.0417   0.8475   1.0000
   0.750   0.2957   0.01830   0.00779  -0.0409   0.8305   1.0000
   1.000   0.3183   0.01845   0.00788  -0.0396   0.8118   1.0000
   1.250   0.3408   0.01859   0.00799  -0.0383   0.7933   1.0000
   1.500   0.3637   0.01869   0.00806  -0.0369   0.7755   1.0000
   1.750   0.3861   0.01880   0.00813  -0.0353   0.7573   1.0000
   2.000   0.4080   0.01894   0.00825  -0.0338   0.7377   1.0000
   2.250   0.4306   0.01903   0.00831  -0.0323   0.7192   1.0000
   2.500   0.4531   0.01913   0.00843  -0.0307   0.7003   1.0000
   2.750   0.4754   0.01927   0.00856  -0.0292   0.6801   1.0000
   3.000   0.4983   0.01938   0.00864  -0.0276   0.6610   1.0000
   3.250   0.5208   0.01956   0.00883  -0.0262   0.6396   1.0000
   3.500   0.5440   0.01972   0.00901  -0.0247   0.6190   1.0000
   3.750   0.5668   0.01996   0.00926  -0.0234   0.5968   1.0000
   4.000   0.5899   0.02017   0.00945  -0.0220   0.5755   1.0000
   4.250   0.6125   0.02047   0.00981  -0.0208   0.5520   1.0000
   4.500   0.6353   0.02076   0.01011  -0.0194   0.5291   1.0000
   4.750   0.6579   0.02109   0.01045  -0.0182   0.5056   1.0000
   5.000   0.6802   0.02149   0.01088  -0.0169   0.4810   1.0000
   5.250   0.7023   0.02190   0.01131  -0.0157   0.4564   1.0000
   5.500   0.7241   0.02235   0.01180  -0.0144   0.4316   1.0000
   5.750   0.7456   0.02285   0.01233  -0.0132   0.4060   1.0000
   6.000   0.7665   0.02340   0.01293  -0.0119   0.3797   1.0000
   6.250   0.7871   0.02401   0.01358  -0.0107   0.3535   1.0000
   6.500   0.8072   0.02468   0.01432  -0.0095   0.3275   1.0000
   6.750   0.8267   0.02541   0.01507  -0.0082   0.3019   1.0000
   7.000   0.8457   0.02621   0.01586  -0.0069   0.2773   1.0000
   7.250   0.8640   0.02711   0.01681  -0.0057   0.2526   1.0000
   7.500   0.8817   0.02809   0.01785  -0.0044   0.2290   1.0000
   7.750   0.8985   0.02916   0.01888  -0.0031   0.2080   1.0000
   8.000   0.9148   0.03034   0.02017  -0.0018   0.1866   1.0000
   8.250   0.9301   0.03160   0.02148  -0.0004   0.1684   1.0000
   8.500   0.9446   0.03297   0.02293   0.0010   0.1507   1.0000
   8.750   0.9589   0.03449   0.02456   0.0024   0.1354   1.0000
   9.000   0.9713   0.03605   0.02622   0.0038   0.1210   1.0000
   9.250   0.9837   0.03777   0.02802   0.0053   0.1093   1.0000
   9.500   0.9943   0.03951   0.02980   0.0068   0.0990   1.0000
   9.750   1.0032   0.04136   0.03183   0.0083   0.0893   1.0000
  10.000   1.0136   0.04372   0.03444   0.0098   0.0820   1.0000
  10.250   1.0210   0.04565   0.03637   0.0112   0.0756   1.0000
  10.500   1.0232   0.04825   0.03939   0.0129   0.0700   1.0000
  10.750   1.0244   0.05065   0.04197   0.0146   0.0656   1.0000
  11.000   1.0305   0.05314   0.04441   0.0158   0.0623   1.0000
  11.250   1.0220   0.05670   0.04841   0.0170   0.0601   1.0000
  11.500   1.0111   0.06054   0.05258   0.0173   0.0581   1.0000
  11.750   0.9987   0.06465   0.05693   0.0169   0.0563   1.0000
  12.000   0.9851   0.06926   0.06175   0.0157   0.0551   1.0000
  12.250   0.9693   0.07454   0.06721   0.0135   0.0543   1.0000
  12.500   0.9412   0.08261   0.07552   0.0091   0.0555   1.0000
  12.750   0.9068   0.09310   0.08618   0.0025   0.0577   1.0000
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