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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 100,000
Max Cl/Cd: 57.86 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh121-il-100000-n5.txt
Download as CSV file: xf-mh121-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4302   0.10789   0.10304  -0.0421   1.0000   0.0386
  -9.000  -0.4360   0.10497   0.10020  -0.0427   1.0000   0.0388
  -8.750  -0.4403   0.10192   0.09723  -0.0424   1.0000   0.0388
  -8.250  -0.3782   0.08886   0.08461  -0.0335   1.0000   0.0338
  -7.750  -0.3988   0.08128   0.07712  -0.0327   1.0000   0.0243
  -7.500  -0.4011   0.07682   0.07271  -0.0341   0.9979   0.0232
  -7.250  -0.4868   0.08417   0.07986  -0.0318   1.0000   0.0244
  -7.000  -0.4886   0.07997   0.07571  -0.0346   0.9982   0.0239
  -6.750  -0.4738   0.07297   0.06868  -0.0442   0.9929   0.0229
  -6.500  -0.4598   0.06594   0.06153  -0.0528   0.9870   0.0216
  -6.250  -0.4412   0.05889   0.05425  -0.0609   0.9822   0.0201
  -6.000  -0.4245   0.05233   0.04736  -0.0663   0.9770   0.0186
  -5.750  -0.4003   0.04552   0.03997  -0.0711   0.9728   0.0169
  -5.500  -0.3701   0.04064   0.03448  -0.0744   0.9701   0.0159
  -5.250  -0.3436   0.03713   0.03046  -0.0760   0.9670   0.0155
  -5.000  -0.3174   0.03403   0.02686  -0.0771   0.9638   0.0154
  -4.750  -0.2881   0.03107   0.02339  -0.0783   0.9614   0.0153
  -4.500  -0.2572   0.02821   0.01989  -0.0795   0.9595   0.0154
  -4.250  -0.2259   0.02577   0.01706  -0.0805   0.9580   0.0157
  -4.000  -0.1946   0.02379   0.01482  -0.0814   0.9567   0.0162
  -3.750  -0.1694   0.02234   0.01323  -0.0811   0.9539   0.0172
  -3.500  -0.1418   0.02123   0.01198  -0.0813   0.9511   0.0191
  -3.250  -0.1117   0.02048   0.01107  -0.0821   0.9485   0.0275
  -3.000  -0.0788   0.01925   0.00977  -0.0834   0.9467   0.0537
  -2.750  -0.0487   0.01701   0.00944  -0.0857   0.9458   0.4637
  -2.500  -0.0183   0.01699   0.00944  -0.0861   0.9436   0.5478
  -2.250   0.0030   0.01705   0.00949  -0.0847   0.9392   0.5989
  -2.000   0.0284   0.01711   0.00947  -0.0840   0.9359   0.6437
  -1.750   0.0579   0.01714   0.00939  -0.0844   0.9332   0.6674
  -1.500   0.0898   0.01715   0.00927  -0.0853   0.9311   0.6834
  -1.250   0.1121   0.01720   0.00924  -0.0844   0.9265   0.6982
  -1.000   0.1401   0.01724   0.00920  -0.0846   0.9230   0.7143
  -0.750   0.1704   0.01727   0.00917  -0.0853   0.9203   0.7312
  -0.500   0.2025   0.01728   0.00909  -0.0863   0.9181   0.7494
   0.000   0.2503   0.01738   0.00922  -0.0850   0.9089   0.7922
   0.250   0.2802   0.01736   0.00926  -0.0854   0.9062   0.8200
   0.500   0.3019   0.01737   0.00936  -0.0842   0.9012   0.8570
   0.750   0.3314   0.01728   0.00941  -0.0846   0.8969   0.9308
   1.000   0.3681   0.01731   0.00940  -0.0868   0.8936   1.0000
   1.250   0.3980   0.01749   0.00955  -0.0877   0.8890   1.0000
   1.500   0.4269   0.01766   0.00972  -0.0883   0.8836   1.0000
   1.750   0.4628   0.01773   0.00982  -0.0901   0.8802   1.0000
   2.000   0.4893   0.01792   0.01010  -0.0901   0.8738   1.0000
   2.250   0.5225   0.01798   0.01022  -0.0913   0.8688   1.0000
   2.500   0.5627   0.01787   0.01021  -0.0937   0.8656   1.0000
   2.750   0.5862   0.01802   0.01046  -0.0929   0.8562   1.0000
   3.000   0.6222   0.01787   0.01045  -0.0943   0.8500   1.0000
   3.250   0.6585   0.01762   0.01048  -0.0955   0.8414   1.0000
   3.500   0.6947   0.01719   0.01025  -0.0963   0.8291   1.0000
   3.750   0.7326   0.01639   0.00966  -0.0967   0.8095   1.0000
   4.000   0.7627   0.01569   0.00914  -0.0957   0.7809   1.0000
   4.250   0.7870   0.01524   0.00885  -0.0937   0.7413   1.0000
   4.500   0.8338   0.01441   0.00758  -0.0946   0.5753   1.0000
   4.750   0.8419   0.01620   0.00802  -0.0905   0.3466   1.0000
   5.000   0.8483   0.01828   0.00917  -0.0873   0.1659   1.0000
   5.250   0.8621   0.02000   0.01036  -0.0851   0.0801   1.0000
   5.500   0.8754   0.02189   0.01178  -0.0828   0.0268   1.0000
   5.750   0.8917   0.02350   0.01349  -0.0806   0.0165   1.0000
   6.000   0.9090   0.02502   0.01517  -0.0787   0.0124   1.0000
   6.250   0.9291   0.02631   0.01662  -0.0774   0.0091   1.0000
   6.500   0.9495   0.02806   0.01855  -0.0761   0.0078   1.0000
   6.750   0.9724   0.03026   0.02097  -0.0752   0.0073   1.0000
   7.000   0.9969   0.03299   0.02401  -0.0745   0.0069   1.0000
   7.250   1.0199   0.03614   0.02756  -0.0735   0.0067   1.0000
   7.500   1.0385   0.03946   0.03134  -0.0719   0.0066   1.0000
   7.750   1.0525   0.04291   0.03526  -0.0697   0.0066   1.0000
   8.000   1.0621   0.04643   0.03924  -0.0671   0.0066   1.0000
   8.250   1.0674   0.05006   0.04332  -0.0642   0.0066   1.0000
   8.500   1.0688   0.05375   0.04742  -0.0610   0.0067   1.0000
   8.750   1.0661   0.05749   0.05154  -0.0576   0.0068   1.0000
   9.000   1.0584   0.06115   0.05553  -0.0539   0.0069   1.0000
   9.250   1.0463   0.06481   0.05947  -0.0502   0.0070   1.0000
   9.500   1.0314   0.06869   0.06359  -0.0471   0.0071   1.0000
   9.750   1.0148   0.07292   0.06805  -0.0449   0.0072   1.0000
  10.000   0.9966   0.07760   0.07293  -0.0439   0.0073   1.0000
  10.250   0.9776   0.08289   0.07839  -0.0443   0.0074   1.0000
  10.500   0.9587   0.08898   0.08463  -0.0462   0.0075   1.0000
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