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MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 91 14.98% (mh91-il)
Reynolds number: 50,000
Max Cl/Cd: 16.06 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh91-il-50000.txt
Download as CSV file: xf-mh91-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 91  14.98%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5274   0.10893   0.10248   0.0022   1.0000   0.1622
 -10.250  -0.5624   0.09536   0.08899  -0.0082   1.0000   0.1311
 -10.000  -0.6403   0.08116   0.07473  -0.0209   1.0000   0.1194
  -9.750  -0.6482   0.07585   0.06942  -0.0220   1.0000   0.1161
  -9.500  -0.6795   0.07066   0.06412  -0.0222   1.0000   0.1130
  -9.250  -0.7524   0.06618   0.05886  -0.0187   1.0000   0.1073
  -9.000  -0.7401   0.06163   0.05429  -0.0184   1.0000   0.1059
  -8.750  -0.7375   0.05759   0.05005  -0.0171   1.0000   0.1044
  -8.500  -0.7357   0.05377   0.04594  -0.0155   1.0000   0.1029
  -8.250  -0.7306   0.05020   0.04202  -0.0137   1.0000   0.1018
  -8.000  -0.7224   0.04684   0.03829  -0.0119   1.0000   0.1015
  -7.750  -0.7105   0.04398   0.03508  -0.0101   1.0000   0.1025
  -7.500  -0.6975   0.04143   0.03213  -0.0083   1.0000   0.1049
  -7.250  -0.6838   0.03927   0.02952  -0.0062   1.0000   0.1072
  -7.000  -0.6603   0.03659   0.02695  -0.0057   1.0000   0.1117
  -6.750  -0.6403   0.03467   0.02492  -0.0043   1.0000   0.1170
  -6.500  -0.6219   0.03285   0.02310  -0.0026   1.0000   0.1247
  -6.250  -0.6065   0.03150   0.02166  -0.0005   1.0000   0.1347
  -6.000  -0.5903   0.03004   0.02033   0.0015   1.0000   0.1499
  -5.750  -0.5783   0.02862   0.01927   0.0039   1.0000   0.1715
  -5.500  -0.5734   0.02727   0.01826   0.0072   1.0000   0.2047
  -5.250  -0.5794   0.02552   0.01730   0.0119   1.0000   0.2744
  -5.000  -0.5980   0.02374   0.01686   0.0191   1.0000   0.4220
  -4.750  -0.6067   0.02353   0.01731   0.0262   1.0000   0.5430
  -4.500  -0.6038   0.02411   0.01817   0.0320   1.0000   0.6171
  -4.250  -0.5958   0.02519   0.01935   0.0375   1.0000   0.6733
  -4.000  -0.5768   0.02711   0.02128   0.0423   0.9981   0.7255
  -3.750  -0.4651   0.03246   0.02617   0.0367   0.9834   0.7899
  -3.500  -0.3013   0.03524   0.02822   0.0180   0.9706   0.8283
  -3.250  -0.1748   0.03551   0.02801   0.0016   0.9544   0.8597
  -3.000  -0.0451   0.03472   0.02681  -0.0163   0.9380   0.8873
  -2.750   0.0519   0.03357   0.02538  -0.0291   0.9177   0.9115
  -2.500   0.1335   0.03229   0.02386  -0.0390   0.8945   0.9332
  -2.250   0.1830   0.03149   0.02291  -0.0435   0.8681   0.9537
  -2.000   0.2297   0.03058   0.02182  -0.0472   0.8439   0.9732
  -1.750   0.2763   0.02959   0.02070  -0.0516   0.8179   0.9925
  -1.500   0.3031   0.02906   0.02005  -0.0524   0.7959   1.0000
  -1.250   0.3148   0.02906   0.01996  -0.0505   0.7768   1.0000
  -1.000   0.3273   0.02910   0.01990  -0.0488   0.7584   1.0000
  -0.750   0.3401   0.02918   0.01989  -0.0471   0.7406   1.0000
  -0.500   0.3536   0.02930   0.01993  -0.0455   0.7234   1.0000
  -0.250   0.3679   0.02949   0.02005  -0.0441   0.7068   1.0000
   0.000   0.3825   0.02972   0.02021  -0.0428   0.6907   1.0000
   0.250   0.3974   0.02999   0.02041  -0.0414   0.6753   1.0000
   0.500   0.4123   0.03023   0.02058  -0.0397   0.6615   1.0000
   0.750   0.4272   0.03033   0.02058  -0.0376   0.6488   1.0000
   1.000   0.4435   0.03083   0.02106  -0.0368   0.6337   1.0000
   1.250   0.4596   0.03142   0.02163  -0.0358   0.6196   1.0000
   1.500   0.4755   0.03181   0.02197  -0.0343   0.6074   1.0000
   1.750   0.4918   0.03206   0.02215  -0.0324   0.5960   1.0000
   2.000   0.5072   0.03299   0.02311  -0.0318   0.5823   1.0000
   2.250   0.5227   0.03364   0.02375  -0.0305   0.5710   1.0000
   2.500   0.5392   0.03397   0.02402  -0.0286   0.5607   1.0000
   2.750   0.5515   0.03534   0.02546  -0.0280   0.5483   1.0000
   3.000   0.5695   0.03546   0.02547  -0.0256   0.5401   1.0000
   3.250   0.5790   0.03706   0.02717  -0.0248   0.5278   1.0000
   3.500   0.5892   0.03844   0.02860  -0.0235   0.5180   1.0000
   3.750   0.6028   0.03924   0.02938  -0.0217   0.5089   1.0000
   4.000   0.6038   0.04154   0.03177  -0.0203   0.4988   1.0000
   4.250   0.6197   0.04205   0.03224  -0.0182   0.4909   1.0000
   4.500   0.6058   0.04557   0.03586  -0.0165   0.4818   1.0000
   4.750   0.6166   0.04655   0.03684  -0.0143   0.4741   1.0000
   5.000   0.5959   0.05017   0.04048  -0.0118   0.4668   1.0000
   5.250   0.5412   0.05586   0.04616  -0.0086   0.4612   1.0000
   5.500   0.6163   0.05250   0.04281  -0.0074   0.4539   1.0000
   5.750   0.5210   0.06114   0.05134  -0.0038   0.4517   1.0000
   6.000   0.4719   0.06575   0.05582  -0.0005   0.4505   1.0000
   6.250   0.4486   0.06959   0.05958   0.0008   0.4496   1.0000
   6.500   0.4395   0.07313   0.06309   0.0011   0.4506   1.0000
   6.750   0.4393   0.07649   0.06644   0.0009   0.4521   1.0000
   7.000   0.4460   0.07978   0.06973   0.0006   0.4534   1.0000
   7.250   0.3331   0.08971   0.07965  -0.0054   0.5634   1.0000
   7.500   0.3541   0.09326   0.08321  -0.0062   0.5576   1.0000
   7.750   0.3550   0.09450   0.08444  -0.0052   0.5448   1.0000
   8.000   0.3597   0.09676   0.08670  -0.0049   0.5358   1.0000
   8.250   0.3851   0.10001   0.08997  -0.0055   0.5250   1.0000
   8.500   0.3772   0.10143   0.09137  -0.0047   0.5161   1.0000
   8.750   0.4097   0.10552   0.09553  -0.0058   0.5068   1.0000
   9.000   0.3980   0.10633   0.09631  -0.0047   0.4951   1.0000
   9.250   0.4342   0.11146   0.10149  -0.0061   0.4882   1.0000
   9.500   0.4174   0.11152   0.10154  -0.0049   0.4767   1.0000
   9.750   0.4410   0.11578   0.10583  -0.0058   0.4699   1.0000
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