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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 50,000
Max Cl/Cd: 33.08 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh64-il-50000-n5.txt
Download as CSV file: xf-mh64-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5552   0.09414   0.08770   0.0012   1.0000   0.0339
  -8.500  -0.5564   0.08911   0.08274  -0.0020   1.0000   0.0331
  -8.250  -0.5594   0.08360   0.07732  -0.0061   1.0000   0.0324
  -8.000  -0.5645   0.07732   0.07111  -0.0117   1.0000   0.0314
  -7.750  -0.5708   0.07004   0.06378  -0.0179   1.0000   0.0304
  -7.500  -0.5769   0.06325   0.05683  -0.0228   1.0000   0.0293
  -7.250  -0.5738   0.05821   0.05137  -0.0252   1.0000   0.0288
  -6.750  -0.5553   0.04954   0.04190  -0.0273   1.0000   0.0284
  -6.250  -0.5265   0.04141   0.03295  -0.0277   1.0000   0.0287
  -6.000  -0.5087   0.03773   0.02887  -0.0276   1.0000   0.0293
  -5.750  -0.4885   0.03467   0.02546  -0.0272   1.0000   0.0302
  -5.500  -0.4669   0.03230   0.02280  -0.0268   1.0000   0.0328
  -5.250  -0.4437   0.03019   0.02032  -0.0261   1.0000   0.0371
  -5.000  -0.4197   0.02801   0.01777  -0.0252   1.0000   0.0409
  -4.750  -0.3975   0.02601   0.01570  -0.0242   1.0000   0.0451
  -4.500  -0.3749   0.02441   0.01391  -0.0231   1.0000   0.0545
  -4.250  -0.3536   0.02275   0.01226  -0.0221   1.0000   0.0710
  -4.000  -0.3319   0.02096   0.01064  -0.0214   1.0000   0.1167
  -3.750  -0.3129   0.01924   0.00968  -0.0207   1.0000   0.2416
  -3.500  -0.2968   0.01843   0.00932  -0.0190   1.0000   0.3531
  -3.250  -0.2809   0.01786   0.00899  -0.0170   1.0000   0.4349
  -3.000  -0.2646   0.01737   0.00864  -0.0149   1.0000   0.5040
  -2.750  -0.2482   0.01691   0.00834  -0.0126   1.0000   0.5713
  -2.500  -0.2321   0.01649   0.00810  -0.0101   1.0000   0.6446
  -2.250  -0.2142   0.01612   0.00793  -0.0076   1.0000   0.7330
  -2.000  -0.1686   0.01583   0.00767  -0.0098   0.9984   0.8702
  -1.750  -0.0905   0.01573   0.00715  -0.0196   0.9958   1.0000
  -1.500  -0.0469   0.01585   0.00689  -0.0237   0.9805   1.0000
  -1.250  -0.0021   0.01598   0.00667  -0.0278   0.9666   1.0000
  -1.000   0.0419   0.01611   0.00655  -0.0315   0.9528   1.0000
  -0.750   0.0830   0.01625   0.00648  -0.0345   0.9381   1.0000
  -0.500   0.1212   0.01640   0.00644  -0.0367   0.9227   1.0000
  -0.250   0.1563   0.01656   0.00646  -0.0383   0.9067   1.0000
   0.000   0.1884   0.01674   0.00652  -0.0390   0.8905   1.0000
   0.250   0.2180   0.01692   0.00660  -0.0392   0.8743   1.0000
   0.500   0.2435   0.01712   0.00673  -0.0386   0.8567   1.0000
   0.750   0.2683   0.01733   0.00686  -0.0377   0.8394   1.0000
   1.000   0.2926   0.01751   0.00699  -0.0366   0.8225   1.0000
   1.250   0.3165   0.01769   0.00711  -0.0354   0.8060   1.0000
   1.500   0.3392   0.01789   0.00731  -0.0341   0.7876   1.0000
   1.750   0.3622   0.01806   0.00746  -0.0327   0.7697   1.0000
   2.000   0.3854   0.01821   0.00759  -0.0312   0.7523   1.0000
   2.250   0.4084   0.01838   0.00777  -0.0299   0.7329   1.0000
   2.500   0.4315   0.01853   0.00792  -0.0285   0.7137   1.0000
   2.750   0.4548   0.01867   0.00813  -0.0270   0.6939   1.0000
   3.000   0.4781   0.01882   0.00832  -0.0257   0.6729   1.0000
   3.250   0.5016   0.01897   0.00850  -0.0243   0.6510   1.0000
   3.500   0.5251   0.01909   0.00864  -0.0228   0.6291   1.0000
   3.750   0.5486   0.01927   0.00887  -0.0216   0.6043   1.0000
   4.000   0.5724   0.01946   0.00916  -0.0203   0.5788   1.0000
   4.250   0.5962   0.01968   0.00941  -0.0190   0.5521   1.0000
   4.500   0.6199   0.01994   0.00969  -0.0178   0.5243   1.0000
   4.750   0.6435   0.02025   0.01002  -0.0166   0.4954   1.0000
   5.000   0.6669   0.02063   0.01039  -0.0154   0.4659   1.0000
   5.250   0.6901   0.02110   0.01096  -0.0144   0.4348   1.0000
   5.500   0.7130   0.02164   0.01153  -0.0134   0.4034   1.0000
   5.750   0.7356   0.02224   0.01214  -0.0124   0.3723   1.0000
   6.000   0.7578   0.02293   0.01284  -0.0115   0.3414   1.0000
   6.250   0.7795   0.02371   0.01367  -0.0106   0.3096   1.0000
   6.500   0.8007   0.02456   0.01456  -0.0098   0.2788   1.0000
   6.750   0.8213   0.02552   0.01552  -0.0089   0.2494   1.0000
   7.000   0.8411   0.02657   0.01670  -0.0080   0.2207   1.0000
   7.250   0.8601   0.02774   0.01791  -0.0071   0.1921   1.0000
   7.500   0.8782   0.02905   0.01924  -0.0062   0.1653   1.0000
   7.750   0.8950   0.03053   0.02074  -0.0053   0.1405   1.0000
   8.000   0.9105   0.03213   0.02241  -0.0044   0.1159   1.0000
   8.250   0.9258   0.03408   0.02443  -0.0033   0.0975   1.0000
   8.500   0.9388   0.03599   0.02644  -0.0023   0.0797   1.0000
   8.750   0.9528   0.03835   0.02895  -0.0010   0.0684   1.0000
   9.000   0.9646   0.04073   0.03147   0.0001   0.0589   1.0000
   9.250   0.9729   0.04294   0.03368   0.0011   0.0510   1.0000
   9.500   0.9848   0.04626   0.03748   0.0024   0.0464   1.0000
   9.750   0.9921   0.04945   0.04098   0.0035   0.0428   1.0000
  10.000   0.9961   0.05226   0.04380   0.0044   0.0395   1.0000
  10.250   0.9901   0.05591   0.04787   0.0054   0.0373   1.0000
  10.500   0.9801   0.05968   0.05198   0.0059   0.0359   1.0000
  10.750   0.9682   0.06396   0.05654   0.0054   0.0352   1.0000
  11.000   0.9532   0.06893   0.06176   0.0036   0.0348   1.0000
  11.250   0.9366   0.07470   0.06772   0.0007   0.0351   1.0000
  11.500   0.9180   0.08144   0.07464  -0.0034   0.0356   1.0000
  11.750   0.8994   0.08904   0.08236  -0.0083   0.0365   1.0000
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