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MH 23 8% (mh23-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 23 8% (mh23-il)
Reynolds number: 500,000
Max Cl/Cd: 66.59 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh23-il-500000-n5.txt
Download as CSV file: xf-mh23-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5021   0.07535   0.07321  -0.0329   1.0000   0.0040
  -8.250  -0.5149   0.07160   0.06951  -0.0348   1.0000   0.0041
  -8.000  -0.5281   0.06725   0.06514  -0.0364   0.9966   0.0040
  -7.750  -0.5218   0.06070   0.05849  -0.0421   0.9913   0.0040
  -7.500  -0.5130   0.05260   0.05020  -0.0465   0.9870   0.0045
  -7.250  -0.5051   0.04562   0.04296  -0.0491   0.9839   0.0047
  -7.000  -0.4895   0.04039   0.03747  -0.0504   0.9817   0.0046
  -6.750  -0.4810   0.03694   0.03377  -0.0502   0.9775   0.0052
  -6.500  -0.4611   0.03611   0.03279  -0.0506   0.9750   0.0062
  -6.250  -0.4430   0.03268   0.02909  -0.0502   0.9723   0.0066
  -6.000  -0.4167   0.03121   0.02746  -0.0501   0.9707   0.0085
  -5.750  -0.4038   0.02687   0.02268  -0.0484   0.9672   0.0076
  -5.500  -0.3895   0.02333   0.01871  -0.0458   0.9629   0.0067
  -5.250  -0.3701   0.01976   0.01462  -0.0437   0.9598   0.0058
  -5.000  -0.3462   0.01724   0.01170  -0.0424   0.9576   0.0052
  -4.750  -0.3202   0.01584   0.01004  -0.0417   0.9559   0.0049
  -4.500  -0.2971   0.01485   0.00890  -0.0406   0.9530   0.0048
  -4.250  -0.2734   0.01397   0.00790  -0.0396   0.9497   0.0047
  -4.000  -0.2488   0.01316   0.00698  -0.0388   0.9466   0.0046
  -3.750  -0.2244   0.01226   0.00598  -0.0379   0.9439   0.0045
  -3.500  -0.2010   0.01162   0.00522  -0.0369   0.9407   0.0044
  -3.250  -0.1792   0.01095   0.00446  -0.0355   0.9364   0.0045
  -3.000  -0.1555   0.01040   0.00381  -0.0345   0.9327   0.0045
  -2.750  -0.1304   0.00999   0.00327  -0.0337   0.9297   0.0047
  -2.500  -0.1063   0.00971   0.00287  -0.0328   0.9250   0.0051
  -2.250  -0.0811   0.00948   0.00256  -0.0320   0.9205   0.0064
  -2.000  -0.0569   0.00902   0.00228  -0.0312   0.9167   0.0550
  -1.750  -0.0388   0.00806   0.00210  -0.0297   0.9110   0.2576
  -1.500  -0.0275   0.00670   0.00192  -0.0268   0.9052   0.5789
  -1.250  -0.0094   0.00616   0.00181  -0.0246   0.8995   0.7023
  -1.000   0.0113   0.00573   0.00179  -0.0226   0.8933   0.8154
  -0.750   0.0460   0.00562   0.00183  -0.0237   0.8891   0.8859
  -0.500   0.0854   0.00568   0.00189  -0.0260   0.8824   0.9168
  -0.250   0.1204   0.00575   0.00193  -0.0272   0.8753   0.9371
   0.000   0.1518   0.00582   0.00198  -0.0277   0.8654   0.9492
   0.250   0.1810   0.00585   0.00198  -0.0278   0.8532   0.9568
   0.500   0.2160   0.00585   0.00193  -0.0293   0.8370   0.9602
   0.750   0.2465   0.00587   0.00186  -0.0297   0.8117   0.9651
   1.000   0.2754   0.00595   0.00178  -0.0297   0.7749   0.9697
   1.250   0.3102   0.00613   0.00176  -0.0311   0.7293   0.9727
   1.500   0.3423   0.00640   0.00180  -0.0321   0.6780   0.9770
   1.750   0.3698   0.00671   0.00190  -0.0321   0.6254   0.9819
   2.000   0.4036   0.00702   0.00196  -0.0336   0.5661   0.9841
   2.250   0.4353   0.00733   0.00204  -0.0348   0.5096   0.9867
   2.500   0.4653   0.00764   0.00214  -0.0356   0.4567   0.9893
   2.750   0.4939   0.00795   0.00226  -0.0361   0.4059   0.9917
   3.250   0.5517   0.00862   0.00257  -0.0373   0.3036   0.9953
   3.500   0.5814   0.00894   0.00273  -0.0381   0.2595   0.9970
   3.750   0.6106   0.00927   0.00290  -0.0388   0.2165   0.9986
   4.000   0.6399   0.00961   0.00310  -0.0395   0.1805   1.0000
   4.250   0.6614   0.00995   0.00335  -0.0385   0.1458   1.0000
   4.500   0.6817   0.01041   0.00362  -0.0373   0.1044   1.0000
   4.750   0.7028   0.01077   0.00389  -0.0361   0.0806   1.0000
   5.000   0.7236   0.01115   0.00419  -0.0350   0.0593   1.0000
   5.250   0.7433   0.01166   0.00455  -0.0336   0.0334   1.0000
   5.500   0.7636   0.01209   0.00491  -0.0324   0.0204   1.0000
   5.750   0.7847   0.01242   0.00526  -0.0312   0.0160   1.0000
   6.000   0.8054   0.01278   0.00565  -0.0299   0.0121   1.0000
   6.250   0.8247   0.01329   0.00619  -0.0284   0.0046   1.0000
   6.500   0.8443   0.01377   0.00671  -0.0270   0.0029   1.0000
   6.750   0.8629   0.01437   0.00739  -0.0252   0.0020   1.0000
   7.000   0.8813   0.01500   0.00815  -0.0235   0.0017   1.0000
   7.250   0.8984   0.01575   0.00905  -0.0215   0.0016   1.0000
   7.500   0.9141   0.01665   0.01012  -0.0193   0.0015   1.0000
   7.750   0.9281   0.01772   0.01136  -0.0168   0.0015   1.0000
   8.000   0.9419   0.01881   0.01261  -0.0143   0.0015   1.0000
   8.250   0.9550   0.01998   0.01397  -0.0118   0.0015   1.0000
   8.500   0.9671   0.02132   0.01550  -0.0091   0.0014   1.0000
   8.750   0.9779   0.02284   0.01725  -0.0063   0.0014   1.0000
   9.000   0.9874   0.02452   0.01917  -0.0034   0.0014   1.0000
   9.250   0.9938   0.02655   0.02150  -0.0001   0.0014   1.0000
   9.500   0.9983   0.02866   0.02389   0.0033   0.0014   1.0000
   9.750   0.9983   0.03109   0.02663   0.0072   0.0014   1.0000
  10.000   0.9943   0.03364   0.02949   0.0113   0.0014   1.0000
  10.250   0.9836   0.03603   0.03215   0.0163   0.0014   1.0000
  10.500   0.9734   0.03836   0.03470   0.0204   0.0014   1.0000
  10.750   0.9578   0.04140   0.03799   0.0241   0.0015   1.0000
  11.000   0.9380   0.04512   0.04196   0.0268   0.0015   1.0000
  11.250   0.9200   0.04907   0.04611   0.0278   0.0015   1.0000
  11.500   0.9061   0.05318   0.05038   0.0271   0.0015   1.0000
  11.750   0.8853   0.05946   0.05684   0.0238   0.0015   1.0000
  12.000   0.8716   0.06625   0.06377   0.0187   0.0015   1.0000
  12.250   0.8509   0.07712   0.07479   0.0106   0.0015   1.0000
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