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MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 94 16.03% (mh94-il)
Reynolds number: 50,000
Max Cl/Cd: 27.28 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh94-il-50000-n5.txt
Download as CSV file: xf-mh94-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 94  16.03%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5738   0.10143   0.09308  -0.0563   1.0000   0.0469
 -13.250  -0.6045   0.09265   0.08417  -0.0607   1.0000   0.0463
 -13.000  -0.6346   0.08510   0.07646  -0.0642   1.0000   0.0458
 -12.750  -0.6607   0.07896   0.07014  -0.0665   1.0000   0.0455
 -12.500  -0.6825   0.07396   0.06495  -0.0676   1.0000   0.0455
 -12.250  -0.7006   0.06977   0.06058  -0.0678   1.0000   0.0457
 -12.000  -0.7158   0.06613   0.05674  -0.0674   1.0000   0.0460
 -11.750  -0.7295   0.06290   0.05331  -0.0663   1.0000   0.0466
 -11.500  -0.7388   0.06007   0.05028  -0.0648   1.0000   0.0470
 -11.250  -0.7502   0.05737   0.04729  -0.0628   1.0000   0.0478
 -11.000  -0.7498   0.05530   0.04514  -0.0609   1.0000   0.0488
 -10.750  -0.7457   0.05355   0.04336  -0.0589   1.0000   0.0500
 -10.500  -0.7415   0.05174   0.04144  -0.0569   1.0000   0.0514
 -10.250  -0.7337   0.04995   0.03947  -0.0548   1.0000   0.0529
 -10.000  -0.7218   0.04827   0.03758  -0.0528   1.0000   0.0547
  -9.750  -0.7120   0.04697   0.03634  -0.0508   1.0000   0.0569
  -9.500  -0.7027   0.04566   0.03494  -0.0485   1.0000   0.0598
  -9.250  -0.6931   0.04440   0.03364  -0.0462   1.0000   0.0629
  -9.000  -0.6871   0.04321   0.03245  -0.0436   1.0000   0.0660
  -8.750  -0.6818   0.04203   0.03118  -0.0407   1.0000   0.0700
  -8.500  -0.6838   0.04085   0.03007  -0.0372   1.0000   0.0733
  -8.250  -0.6848   0.03976   0.02888  -0.0335   1.0000   0.0779
  -8.000  -0.6891   0.03856   0.02778  -0.0296   1.0000   0.0820
  -7.750  -0.6900   0.03738   0.02658  -0.0260   1.0000   0.0885
  -7.500  -0.6928   0.03608   0.02536  -0.0223   1.0000   0.0957
  -7.250  -0.6948   0.03475   0.02412  -0.0187   1.0000   0.1052
  -7.000  -0.6962   0.03335   0.02284  -0.0152   1.0000   0.1193
  -6.750  -0.6977   0.03183   0.02155  -0.0117   1.0000   0.1410
  -6.500  -0.6988   0.03020   0.02029  -0.0085   1.0000   0.1787
  -6.250  -0.6985   0.02867   0.01922  -0.0053   1.0000   0.2369
  -6.000  -0.6941   0.02757   0.01856  -0.0024   1.0000   0.3049
  -5.750  -0.6855   0.02695   0.01824   0.0004   1.0000   0.3656
  -5.500  -0.6742   0.02668   0.01816   0.0031   1.0000   0.4160
  -5.250  -0.6616   0.02661   0.01815   0.0057   1.0000   0.4594
  -5.000  -0.6482   0.02672   0.01830   0.0084   1.0000   0.4973
  -4.750  -0.6336   0.02706   0.01869   0.0113   1.0000   0.5278
  -4.500  -0.6120   0.02738   0.01895   0.0126   0.9974   0.5557
  -4.250  -0.5789   0.02796   0.01944   0.0120   0.9905   0.5778
  -4.000  -0.5450   0.02836   0.01969   0.0110   0.9835   0.5965
  -3.750  -0.5134   0.02859   0.01977   0.0103   0.9758   0.6135
  -3.500  -0.4801   0.02881   0.01984   0.0091   0.9685   0.6301
  -3.250  -0.4487   0.02909   0.02002   0.0087   0.9604   0.6441
  -3.000  -0.4172   0.02933   0.02016   0.0082   0.9524   0.6573
  -2.750  -0.3843   0.02946   0.02017   0.0071   0.9444   0.6715
  -2.500  -0.3562   0.02946   0.02005   0.0068   0.9351   0.6855
  -2.250  -0.3194   0.02974   0.02026   0.0055   0.9277   0.6964
  -2.000  -0.2939   0.02965   0.02007   0.0057   0.9172   0.7091
  -1.750  -0.2607   0.02974   0.02010   0.0048   0.9087   0.7206
  -1.500  -0.2306   0.02974   0.02003   0.0044   0.8987   0.7316
  -1.250  -0.2029   0.02964   0.01984   0.0041   0.8883   0.7442
  -1.000  -0.1660   0.02971   0.01989   0.0029   0.8799   0.7537
  -0.750  -0.1417   0.02956   0.01967   0.0032   0.8678   0.7661
  -0.500  -0.1048   0.02957   0.01965   0.0020   0.8593   0.7755
  -0.250  -0.0787   0.02942   0.01947   0.0022   0.8471   0.7871
   0.000  -0.0505   0.02936   0.01939   0.0024   0.8354   0.7975
   0.250  -0.0121   0.02914   0.01915   0.0009   0.8265   0.8080
   0.500   0.0119   0.02902   0.01901   0.0017   0.8127   0.8192
   0.750   0.0436   0.02884   0.01884   0.0014   0.8009   0.8292
   1.000   0.0808   0.02845   0.01844   0.0003   0.7908   0.8405
   1.250   0.1101   0.02829   0.01830   0.0005   0.7766   0.8500
   1.500   0.1412   0.02796   0.01798   0.0004   0.7638   0.8614
   1.750   0.1892   0.02749   0.01752  -0.0022   0.7534   0.8696
   2.250   0.2557   0.02691   0.01700  -0.0031   0.7218   0.8904
   2.500   0.2955   0.02656   0.01667  -0.0046   0.7056   0.8997
   2.750   0.3368   0.02621   0.01633  -0.0064   0.6881   0.9093
   3.000   0.3808   0.02588   0.01600  -0.0087   0.6684   0.9175
   3.250   0.4206   0.02557   0.01568  -0.0103   0.6469   0.9271
   3.500   0.4703   0.02526   0.01533  -0.0135   0.6228   0.9339
   3.750   0.5054   0.02518   0.01523  -0.0147   0.5950   0.9440
   4.000   0.5514   0.02508   0.01500  -0.0176   0.5645   0.9511
   4.250   0.5890   0.02514   0.01496  -0.0194   0.5312   0.9602
   4.750   0.6602   0.02556   0.01512  -0.0229   0.4618   0.9799
   5.000   0.6937   0.02591   0.01531  -0.0245   0.4276   0.9909
   5.250   0.7174   0.02630   0.01553  -0.0245   0.3989   1.0000
   5.500   0.7162   0.02653   0.01566  -0.0200   0.3804   1.0000
   5.750   0.7144   0.02678   0.01582  -0.0154   0.3628   1.0000
   6.000   0.7140   0.02707   0.01601  -0.0110   0.3457   1.0000
   6.250   0.7173   0.02746   0.01628  -0.0073   0.3284   1.0000
   6.500   0.7249   0.02796   0.01667  -0.0044   0.3109   1.0000
   6.750   0.7359   0.02855   0.01716  -0.0021   0.2938   1.0000
   7.000   0.7485   0.02922   0.01773  -0.0002   0.2773   1.0000
   7.250   0.7632   0.02997   0.01838   0.0014   0.2621   1.0000
   7.500   0.7791   0.03076   0.01910   0.0028   0.2484   1.0000
   7.750   0.7961   0.03159   0.01979   0.0039   0.2363   1.0000
   8.000   0.8134   0.03248   0.02069   0.0050   0.2242   1.0000
   8.250   0.8325   0.03342   0.02163   0.0058   0.2141   1.0000
   8.500   0.8514   0.03435   0.02248   0.0066   0.2052   1.0000
   8.750   0.8699   0.03540   0.02359   0.0074   0.1966   1.0000
   9.000   0.8897   0.03640   0.02454   0.0081   0.1896   1.0000
   9.250   0.9096   0.03756   0.02576   0.0086   0.1833   1.0000
   9.500   0.9272   0.03872   0.02701   0.0094   0.1772   1.0000
   9.750   0.9499   0.03978   0.02797   0.0096   0.1723   1.0000
  10.000   0.9634   0.04123   0.02963   0.0108   0.1673   1.0000
  10.250   0.9786   0.04265   0.03118   0.0118   0.1630   1.0000
  10.500   0.9970   0.04394   0.03249   0.0123   0.1593   1.0000
  10.750   1.0168   0.04533   0.03388   0.0127   0.1560   1.0000
  11.000   1.0202   0.04730   0.03614   0.0146   0.1527   1.0000
  11.250   1.0255   0.04923   0.03827   0.0161   0.1497   1.0000
  11.500   1.0334   0.05104   0.04020   0.0173   0.1469   1.0000
  11.750   1.0458   0.05276   0.04200   0.0180   0.1446   1.0000
  12.000   1.0647   0.05436   0.04356   0.0183   0.1424   1.0000
  12.250   1.0489   0.05756   0.04711   0.0205   0.1408   1.0000
  12.500   1.0295   0.06129   0.05115   0.0221   0.1394   1.0000
  12.750   1.0041   0.06585   0.05601   0.0229   0.1382   1.0000
  13.000   0.9654   0.07221   0.06266   0.0224   0.1371   1.0000
  13.250   0.8028   0.09895   0.08989   0.0090   0.1372   1.0000
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