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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 100,000
Max Cl/Cd: 33.41 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du861372-il-100000.txt
Download as CSV file: xf-du861372-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU 86-137/25 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.8082   0.04972   0.04200  -0.0257   0.4160   0.1091
  -8.500  -0.8107   0.04399   0.03498  -0.0210   0.4161   0.0903
  -8.250  -0.7837   0.04011   0.03093  -0.0209   0.4162   0.0846
  -8.000  -0.7651   0.03793   0.02788  -0.0184   0.4162   0.0776
  -7.750  -0.7340   0.03496   0.02476  -0.0188   0.4162   0.0749
  -7.500  -0.7026   0.03254   0.02210  -0.0190   0.4164   0.0721
  -7.250  -0.6694   0.03065   0.01997  -0.0193   0.4165   0.0698
  -7.000  -0.6361   0.02909   0.01830  -0.0198   0.4170   0.0696
  -6.750  -0.6037   0.02773   0.01689  -0.0202   0.4176   0.0698
  -6.500  -0.5737   0.02656   0.01570  -0.0203   0.4184   0.0693
  -6.250  -0.5493   0.02555   0.01468  -0.0196   0.4193   0.0690
  -6.000  -0.5300   0.02465   0.01376  -0.0182   0.4201   0.0690
  -5.750  -0.5130   0.02382   0.01287  -0.0166   0.4212   0.0694
  -5.500  -0.4960   0.02306   0.01204  -0.0150   0.4223   0.0703
  -5.250  -0.4782   0.02235   0.01124  -0.0135   0.4235   0.0718
  -5.000  -0.4592   0.02171   0.01050  -0.0122   0.4248   0.0744
  -4.750  -0.4402   0.02103   0.00979  -0.0108   0.4262   0.0803
  -4.500  -0.4249   0.02003   0.00918  -0.0091   0.4276   0.1390
  -4.250  -0.4069   0.01927   0.00861  -0.0077   0.4291   0.1916
  -4.000  -0.4029   0.01762   0.00796  -0.0046   0.4306   0.3726
  -3.750  -0.3901   0.01679   0.00777  -0.0020   0.4322   0.4954
  -3.500  -0.3674   0.01671   0.00808  -0.0003   0.4343   0.5771
  -3.250  -0.3416   0.01676   0.00816   0.0005   0.4369   0.6116
  -3.000  -0.3161   0.01675   0.00812   0.0012   0.4397   0.6342
  -2.750  -0.2909   0.01674   0.00806   0.0018   0.4427   0.6522
  -2.500  -0.2658   0.01675   0.00802   0.0024   0.4458   0.6691
  -2.250  -0.2406   0.01689   0.00815   0.0032   0.4491   0.6892
  -2.000  -0.2157   0.01687   0.00809   0.0037   0.4530   0.7034
  -1.750  -0.1894   0.01686   0.00805   0.0041   0.4574   0.7115
  -1.500  -0.1641   0.01692   0.00807   0.0047   0.4620   0.7235
  -1.250  -0.1393   0.01704   0.00819   0.0055   0.4667   0.7378
  -1.000  -0.1147   0.01716   0.00832   0.0063   0.4723   0.7523
  -0.750  -0.0872   0.01739   0.00860   0.0070   0.4783   0.7613
  -0.500  -0.0621   0.01744   0.00868   0.0077   0.4846   0.7717
  -0.250  -0.0373   0.01777   0.00910   0.0091   0.4918   0.7876
   0.250   0.0166   0.01812   0.00964   0.0108   0.5087   0.8078
   0.500   0.0397   0.01818   0.00977   0.0119   0.5171   0.8200
   0.750   0.0714   0.01843   0.01016   0.0121   0.5277   0.8289
   1.000   0.0970   0.01852   0.01036   0.0130   0.5362   0.8402
   1.250   0.1364   0.01911   0.01108   0.0127   0.5431   0.8598
   1.500   0.1704   0.01931   0.01131   0.0123   0.5428   0.8736
   1.750   0.2036   0.01934   0.01137   0.0114   0.5406   0.8822
   2.000   0.3928   0.02012   0.01241  -0.0157   0.5537   0.9474
   2.500   0.4483   0.01957   0.01193  -0.0170   0.5442   0.9559
   2.750   0.4770   0.01933   0.01175  -0.0179   0.5383   0.9600
   3.000   0.5007   0.01920   0.01164  -0.0177   0.5293   0.9645
   3.250   0.5246   0.01908   0.01147  -0.0176   0.5116   0.9682
   3.500   0.5543   0.01894   0.01125  -0.0185   0.4851   0.9718
   3.750   0.5804   0.01894   0.01117  -0.0189   0.4555   0.9759
   4.000   0.6011   0.01913   0.01121  -0.0182   0.4223   0.9796
   4.250   0.6223   0.01950   0.01130  -0.0178   0.3946   0.9829
   4.500   0.6525   0.01953   0.01148  -0.0190   0.3290   0.9865
   4.750   0.6688   0.02194   0.01241  -0.0178   0.3101   0.9892
   5.000   0.7079   0.02617   0.01620  -0.0207   0.2749   0.9903
   5.250   0.7288   0.02775   0.01814  -0.0205   0.2480   0.9929
   5.500   0.7493   0.02709   0.01809  -0.0200   0.2211   0.9970
   5.750   0.7670   0.02589   0.01740  -0.0188   0.1938   1.0000
   6.000   0.7729   0.02509   0.01699  -0.0157   0.1808   1.0000
   6.250   0.7786   0.02488   0.01698  -0.0127   0.1665   1.0000
   6.500   0.7832   0.02568   0.01772  -0.0095   0.1497   1.0000
   6.750   0.7869   0.02665   0.01865  -0.0061   0.1360   1.0000
   7.000   0.7887   0.02761   0.01950  -0.0025   0.1258   1.0000
   7.250   0.7971   0.02828   0.02021   0.0004   0.1145   1.0000
   7.500   0.8054   0.02928   0.02114   0.0033   0.1066   1.0000
   7.750   0.8161   0.03008   0.02193   0.0059   0.0992   1.0000
   8.000   0.8294   0.03134   0.02312   0.0079   0.0923   1.0000
   8.250   0.8448   0.03246   0.02436   0.0098   0.0865   1.0000
   8.500   0.8589   0.03386   0.02570   0.0116   0.0822   1.0000
   8.750   0.8787   0.03606   0.02806   0.0127   0.0780   1.0000
   9.000   0.8873   0.03747   0.02973   0.0156   0.0747   1.0000
   9.250   0.8928   0.03898   0.03142   0.0187   0.0721   1.0000
   9.500   0.8961   0.04068   0.03331   0.0221   0.0708   1.0000
   9.750   0.8959   0.04241   0.03522   0.0258   0.0696   1.0000
  10.000   0.8976   0.04466   0.03768   0.0289   0.0688   1.0000
  10.250   0.9023   0.04760   0.04084   0.0308   0.0677   1.0000
  10.500   0.9043   0.05142   0.04491   0.0323   0.0669   1.0000
  11.000   0.8884   0.05964   0.05372   0.0362   0.0660   1.0000
  11.250   0.8751   0.06332   0.05763   0.0383   0.0660   1.0000
  11.500   0.8579   0.06711   0.06161   0.0402   0.0661   1.0000
  11.750   0.8399   0.07020   0.06494   0.0414   0.0666   1.0000
  12.000   0.7187   0.08569   0.08096   0.0358   0.0776   1.0000
  12.250   0.7069   0.09190   0.08717   0.0335   0.0791   1.0000
  12.500   0.7122   0.09702   0.09228   0.0330   0.0802   1.0000
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