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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 100,000
Max Cl/Cd: 45.17 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh64-il-100000-n5.txt
Download as CSV file: xf-mh64-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 64  8.59%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5646   0.08986   0.08528   0.0040   1.0000   0.0150
  -8.500  -0.5664   0.08483   0.08030   0.0009   1.0000   0.0147
  -8.250  -0.5698   0.07943   0.07498  -0.0028   1.0000   0.0144
  -8.000  -0.5750   0.07369   0.06930  -0.0076   1.0000   0.0141
  -7.750  -0.5797   0.06635   0.06196  -0.0146   1.0000   0.0138
  -7.500  -0.5819   0.05929   0.05483  -0.0196   1.0000   0.0134
  -7.250  -0.5817   0.05287   0.04816  -0.0230   1.0000   0.0130
  -7.000  -0.5772   0.04698   0.04191  -0.0251   1.0000   0.0127
  -6.750  -0.5677   0.04172   0.03616  -0.0261   1.0000   0.0124
  -6.500  -0.5538   0.03718   0.03100  -0.0263   1.0000   0.0122
  -6.250  -0.5361   0.03350   0.02680  -0.0261   1.0000   0.0121
  -6.000  -0.5159   0.03038   0.02320  -0.0257   1.0000   0.0122
  -5.750  -0.4939   0.02774   0.02014  -0.0252   1.0000   0.0123
  -5.500  -0.4707   0.02550   0.01755  -0.0246   1.0000   0.0127
  -5.250  -0.4470   0.02382   0.01561  -0.0241   1.0000   0.0140
  -5.000  -0.4230   0.02246   0.01403  -0.0235   1.0000   0.0165
  -4.750  -0.3993   0.02126   0.01261  -0.0227   1.0000   0.0182
  -4.500  -0.3799   0.01952   0.01080  -0.0214   1.0000   0.0198
  -4.250  -0.3621   0.01836   0.00956  -0.0199   1.0000   0.0226
  -4.000  -0.3307   0.01724   0.00821  -0.0209   0.9871   0.0302
  -3.750  -0.2969   0.01560   0.00679  -0.0224   0.9742   0.0736
  -3.500  -0.2650   0.01422   0.00618  -0.0241   0.9620   0.2274
  -3.250  -0.2325   0.01358   0.00591  -0.0254   0.9500   0.3318
  -3.000  -0.2010   0.01316   0.00565  -0.0261   0.9380   0.4068
  -2.750  -0.1709   0.01283   0.00543  -0.0264   0.9260   0.4699
  -2.500  -0.1426   0.01254   0.00519  -0.0261   0.9139   0.5307
  -2.250  -0.1158   0.01228   0.00504  -0.0255   0.9016   0.5930
  -2.000  -0.0906   0.01203   0.00492  -0.0243   0.8892   0.6595
  -1.750  -0.0655   0.01179   0.00483  -0.0230   0.8771   0.7329
  -1.500  -0.0363   0.01159   0.00475  -0.0222   0.8656   0.8140
  -1.250   0.0061   0.01146   0.00459  -0.0242   0.8552   0.8942
  -1.000   0.0525   0.01138   0.00439  -0.0274   0.8442   0.9541
  -0.750   0.0975   0.01133   0.00417  -0.0307   0.8326   0.9955
  -0.500   0.1223   0.01138   0.00404  -0.0301   0.8191   1.0000
  -0.250   0.1450   0.01143   0.00397  -0.0289   0.8055   1.0000
   0.000   0.1680   0.01150   0.00391  -0.0278   0.7919   1.0000
   0.250   0.1914   0.01156   0.00387  -0.0267   0.7782   1.0000
   0.500   0.2152   0.01163   0.00384  -0.0258   0.7642   1.0000
   0.750   0.2393   0.01171   0.00383  -0.0248   0.7497   1.0000
   1.000   0.2637   0.01178   0.00383  -0.0239   0.7347   1.0000
   1.250   0.2883   0.01186   0.00384  -0.0231   0.7191   1.0000
   1.500   0.3130   0.01195   0.00387  -0.0223   0.7030   1.0000
   1.750   0.3379   0.01203   0.00391  -0.0214   0.6864   1.0000
   2.000   0.3627   0.01212   0.00393  -0.0206   0.6694   1.0000
   2.250   0.3881   0.01223   0.00401  -0.0199   0.6499   1.0000
   2.500   0.4133   0.01234   0.00406  -0.0191   0.6303   1.0000
   2.750   0.4387   0.01246   0.00420  -0.0185   0.6087   1.0000
   3.000   0.4640   0.01261   0.00429  -0.0177   0.5864   1.0000
   3.250   0.4894   0.01278   0.00442  -0.0171   0.5622   1.0000
   3.500   0.5147   0.01297   0.00457  -0.0164   0.5365   1.0000
   3.750   0.5401   0.01320   0.00479  -0.0158   0.5096   1.0000
   4.000   0.5653   0.01347   0.00500  -0.0152   0.4820   1.0000
   4.250   0.5905   0.01378   0.00525  -0.0146   0.4539   1.0000
   4.500   0.6155   0.01412   0.00555  -0.0141   0.4256   1.0000
   4.750   0.6405   0.01450   0.00588  -0.0136   0.3973   1.0000
   5.000   0.6654   0.01491   0.00632  -0.0131   0.3686   1.0000
   5.250   0.6902   0.01535   0.00675  -0.0127   0.3398   1.0000
   5.500   0.7148   0.01583   0.00721  -0.0122   0.3111   1.0000
   5.750   0.7390   0.01636   0.00772  -0.0118   0.2819   1.0000
   6.000   0.7631   0.01693   0.00828  -0.0113   0.2534   1.0000
   6.250   0.7867   0.01755   0.00890  -0.0109   0.2251   1.0000
   6.500   0.8100   0.01824   0.00957  -0.0104   0.1976   1.0000
   6.750   0.8329   0.01898   0.01039  -0.0099   0.1713   1.0000
   7.000   0.8553   0.01980   0.01121  -0.0094   0.1457   1.0000
   7.250   0.8771   0.02070   0.01210  -0.0089   0.1210   1.0000
   7.500   0.8981   0.02171   0.01311  -0.0083   0.0984   1.0000
   7.750   0.9180   0.02288   0.01423  -0.0077   0.0757   1.0000
   8.000   0.9372   0.02416   0.01557  -0.0069   0.0574   1.0000
   8.250   0.9547   0.02563   0.01708  -0.0061   0.0436   1.0000
   8.500   0.9696   0.02747   0.01901  -0.0048   0.0358   1.0000
   8.750   0.9829   0.02932   0.02091  -0.0038   0.0283   1.0000
   9.000   0.9974   0.03117   0.02303  -0.0024   0.0242   1.0000
   9.250   1.0094   0.03301   0.02499  -0.0013   0.0202   1.0000
   9.500   1.0180   0.03536   0.02751   0.0001   0.0176   1.0000
   9.750   1.0275   0.03775   0.03030   0.0016   0.0159   1.0000
  10.000   1.0341   0.04041   0.03324   0.0031   0.0148   1.0000
  10.250   1.0363   0.04308   0.03617   0.0046   0.0138   1.0000
  10.500   1.0345   0.04566   0.03896   0.0061   0.0131   1.0000
  10.750   1.0305   0.04839   0.04187   0.0069   0.0126   1.0000
  11.000   1.0235   0.05150   0.04513   0.0070   0.0119   1.0000
  11.250   1.0146   0.05535   0.04918   0.0064   0.0116   1.0000
  12.000   0.9713   0.07148   0.06589  -0.0011   0.0110   1.0000
  12.750   0.9245   0.09401   0.08915  -0.0158   0.0123   1.0000
  13.000   0.8847   0.10964   0.10500  -0.0255   0.0141   1.0000
  13.250   0.8590   0.12230   0.11760  -0.0325   0.0151   1.0000
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