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MH 23 8% (mh23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 23 8% (mh23-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.2 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh23-il-1000000-n5.txt
Download as CSV file: xf-mh23-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 23  8%                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5129   0.07807   0.07654  -0.0308   1.0000   0.0020
  -8.750  -0.5204   0.07412   0.07262  -0.0336   1.0000   0.0022
  -8.500  -0.5242   0.06611   0.06460  -0.0435   0.9879   0.0020
  -8.250  -0.5189   0.05940   0.05778  -0.0508   0.9813   0.0022
  -8.000  -0.5155   0.05360   0.05186  -0.0540   0.9739   0.0022
  -7.750  -0.5118   0.04850   0.04660  -0.0551   0.9680   0.0023
  -7.500  -0.5028   0.04609   0.04408  -0.0547   0.9630   0.0025
  -7.250  -0.4961   0.04241   0.04024  -0.0537   0.9585   0.0027
  -7.000  -0.4894   0.03825   0.03586  -0.0521   0.9547   0.0028
  -6.750  -0.4795   0.03454   0.03194  -0.0504   0.9509   0.0030
  -6.500  -0.4690   0.03073   0.02787  -0.0481   0.9472   0.0032
  -6.250  -0.4578   0.02704   0.02387  -0.0456   0.9440   0.0032
  -6.000  -0.4427   0.02411   0.02061  -0.0435   0.9412   0.0033
  -5.750  -0.4250   0.02171   0.01794  -0.0417   0.9382   0.0035
  -5.500  -0.4021   0.02073   0.01681  -0.0407   0.9358   0.0040
  -4.750  -0.3386   0.01583   0.01119  -0.0365   0.9281   0.0042
  -4.500  -0.3168   0.01366   0.00874  -0.0351   0.9247   0.0039
  -4.250  -0.2932   0.01228   0.00719  -0.0340   0.9217   0.0038
  -4.000  -0.2696   0.01118   0.00595  -0.0329   0.9188   0.0037
  -3.750  -0.2465   0.01022   0.00486  -0.0317   0.9159   0.0035
  -3.500  -0.2224   0.00953   0.00408  -0.0308   0.9124   0.0035
  -3.250  -0.1983   0.00893   0.00335  -0.0299   0.9085   0.0034
  -3.000  -0.1735   0.00848   0.00280  -0.0291   0.9049   0.0033
  -2.750  -0.1480   0.00814   0.00238  -0.0285   0.9013   0.0033
  -2.500  -0.1218   0.00787   0.00205  -0.0280   0.8969   0.0033
  -2.250  -0.0954   0.00767   0.00178  -0.0276   0.8924   0.0034
  -2.000  -0.0689   0.00750   0.00156  -0.0273   0.8877   0.0036
  -1.750  -0.0420   0.00736   0.00139  -0.0270   0.8817   0.0053
  -1.500  -0.0177   0.00691   0.00119  -0.0263   0.8759   0.0829
  -1.250   0.0050   0.00627   0.00105  -0.0256   0.8677   0.2320
  -1.000   0.0238   0.00534   0.00092  -0.0242   0.8581   0.4741
  -0.750   0.0466   0.00494   0.00083  -0.0232   0.8457   0.5771
  -0.500   0.0689   0.00461   0.00074  -0.0220   0.8280   0.6683
  -0.250   0.0895   0.00429   0.00064  -0.0204   0.8032   0.7629
   0.000   0.1103   0.00413   0.00063  -0.0186   0.7710   0.8456
   0.250   0.1357   0.00418   0.00072  -0.0179   0.7347   0.9043
   0.500   0.1657   0.00442   0.00085  -0.0182   0.6935   0.9343
   0.750   0.1927   0.00467   0.00095  -0.0180   0.6522   0.9473
   1.000   0.2164   0.00490   0.00102  -0.0171   0.6120   0.9560
   1.250   0.2453   0.00516   0.00110  -0.0174   0.5683   0.9599
   1.500   0.2714   0.00541   0.00119  -0.0171   0.5248   0.9650
   1.750   0.2966   0.00566   0.00128  -0.0166   0.4837   0.9695
   2.000   0.3300   0.00594   0.00140  -0.0181   0.4383   0.9718
   2.250   0.3652   0.00625   0.00152  -0.0200   0.3929   0.9745
   2.500   0.3974   0.00654   0.00165  -0.0212   0.3527   0.9781
   2.750   0.4244   0.00682   0.00179  -0.0212   0.3141   0.9819
   3.250   0.4891   0.00738   0.00207  -0.0238   0.2353   0.9839
   3.500   0.5198   0.00766   0.00221  -0.0247   0.1990   0.9851
   3.750   0.5498   0.00792   0.00236  -0.0255   0.1702   0.9863
   4.000   0.5789   0.00818   0.00253  -0.0261   0.1435   0.9876
   4.250   0.6066   0.00855   0.00273  -0.0264   0.1057   0.9890
   4.500   0.6337   0.00893   0.00298  -0.0266   0.0741   0.9905
   4.750   0.6587   0.00948   0.00329  -0.0265   0.0311   0.9920
   5.000   0.6849   0.00980   0.00355  -0.0264   0.0192   0.9933
   5.250   0.7127   0.01007   0.00379  -0.0267   0.0126   0.9942
   5.500   0.7414   0.01034   0.00405  -0.0271   0.0085   0.9949
   5.750   0.7689   0.01079   0.00445  -0.0274   0.0016   0.9957
   6.000   0.7974   0.01109   0.00479  -0.0278   0.0013   0.9966
   6.250   0.8253   0.01145   0.00525  -0.0281   0.0011   0.9975
   6.500   0.8527   0.01181   0.00568  -0.0283   0.0010   0.9984
   6.750   0.8798   0.01229   0.00625  -0.0284   0.0010   0.9992
   7.000   0.9066   0.01280   0.00685  -0.0285   0.0009   1.0000
   7.250   0.9261   0.01332   0.00747  -0.0270   0.0009   1.0000
   7.500   0.9445   0.01390   0.00815  -0.0253   0.0009   1.0000
   7.750   0.9612   0.01465   0.00902  -0.0232   0.0009   1.0000
   8.000   0.9770   0.01546   0.00997  -0.0210   0.0009   1.0000
   8.250   0.9920   0.01634   0.01099  -0.0187   0.0009   1.0000
   8.500   1.0055   0.01736   0.01217  -0.0162   0.0009   1.0000
   8.750   1.0176   0.01853   0.01352  -0.0134   0.0009   1.0000
   9.000   1.0287   0.01980   0.01497  -0.0105   0.0009   1.0000
   9.250   1.0367   0.02145   0.01686  -0.0071   0.0009   1.0000
   9.500   1.0443   0.02309   0.01872  -0.0038   0.0009   1.0000
   9.750   1.0483   0.02511   0.02106  -0.0001   0.0010   1.0000
  10.000   1.0488   0.02738   0.02362   0.0040   0.0010   1.0000
  10.250   1.0454   0.02984   0.02637   0.0084   0.0010   1.0000
  10.500   1.0399   0.03191   0.02866   0.0129   0.0010   1.0000
  10.750   1.0240   0.03447   0.03147   0.0186   0.0010   1.0000
  11.000   1.0043   0.03765   0.03491   0.0235   0.0010   1.0000
  11.250   0.9879   0.04075   0.03823   0.0268   0.0010   1.0000
  11.500   0.9759   0.04367   0.04130   0.0287   0.0010   1.0000
  11.750   0.9526   0.04838   0.04622   0.0293   0.0010   1.0000
  12.000   0.9403   0.05252   0.05049   0.0281   0.0010   1.0000
  12.250   0.9159   0.06005   0.05820   0.0233   0.0010   1.0000
  12.500   0.9028   0.06760   0.06588   0.0173   0.0010   1.0000
  12.750   0.8744   0.08164   0.08007   0.0075   0.0010   1.0000
  13.000   0.8563   0.09185   0.09029   0.0026   0.0010   1.0000
  13.250   0.8324   0.10247   0.10093  -0.0019   0.0010   1.0000
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