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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 100,000
Max Cl/Cd: 33.87 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-100000.txt
Download as CSV file: xf-joukowsk0009-jf-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.7124   0.11182   0.10693   0.0229   1.0000   0.1469
  -9.750  -0.8126   0.07698   0.07214  -0.0056   1.0000   0.0796
  -9.500  -0.8146   0.07199   0.06708  -0.0067   1.0000   0.0771
  -9.250  -0.8251   0.06641   0.06141  -0.0085   1.0000   0.0757
  -9.000  -0.8393   0.05996   0.05474  -0.0106   1.0000   0.0736
  -8.750  -0.8536   0.05251   0.04678  -0.0122   1.0000   0.0708
  -8.500  -0.8628   0.04480   0.03810  -0.0127   1.0000   0.0682
  -8.250  -0.8508   0.04051   0.03332  -0.0123   1.0000   0.0685
  -8.000  -0.8325   0.03746   0.03003  -0.0120   1.0000   0.0703
  -7.750  -0.8130   0.03502   0.02727  -0.0115   1.0000   0.0740
  -7.500  -0.7930   0.03226   0.02389  -0.0108   1.0000   0.0772
  -7.250  -0.7710   0.02926   0.02049  -0.0103   1.0000   0.0801
  -7.000  -0.7472   0.02753   0.01874  -0.0099   1.0000   0.0860
  -6.750  -0.7226   0.02571   0.01653  -0.0093   1.0000   0.0924
  -6.500  -0.6978   0.02390   0.01481  -0.0089   1.0000   0.1000
  -6.250  -0.6730   0.02239   0.01324  -0.0084   1.0000   0.1105
  -6.000  -0.6480   0.02097   0.01180  -0.0078   1.0000   0.1231
  -5.750  -0.6234   0.01976   0.01067  -0.0073   1.0000   0.1407
  -5.500  -0.5989   0.01854   0.00954  -0.0068   1.0000   0.1641
  -5.250  -0.5749   0.01741   0.00862  -0.0063   1.0000   0.1962
  -5.000  -0.5510   0.01640   0.00785  -0.0057   1.0000   0.2399
  -4.750  -0.5270   0.01556   0.00725  -0.0052   1.0000   0.2928
  -4.500  -0.5030   0.01488   0.00685  -0.0046   1.0000   0.3453
  -4.250  -0.4784   0.01438   0.00650  -0.0039   1.0000   0.3975
  -4.000  -0.4539   0.01396   0.00627  -0.0031   1.0000   0.4446
  -3.750  -0.4293   0.01362   0.00606  -0.0022   1.0000   0.4890
  -3.500  -0.4049   0.01332   0.00590  -0.0012   1.0000   0.5299
  -3.250  -0.3807   0.01306   0.00577  -0.0001   1.0000   0.5685
  -3.000  -0.3567   0.01282   0.00565   0.0011   1.0000   0.6060
  -2.750  -0.3331   0.01260   0.00555   0.0025   1.0000   0.6415
  -2.500  -0.3102   0.01240   0.00546   0.0040   1.0000   0.6749
  -2.250  -0.2882   0.01221   0.00539   0.0057   1.0000   0.7078
  -2.000  -0.2673   0.01204   0.00533   0.0077   1.0000   0.7401
  -1.750  -0.2479   0.01187   0.00528   0.0099   1.0000   0.7723
  -1.500  -0.2303   0.01172   0.00522   0.0124   1.0000   0.8050
  -1.250  -0.2141   0.01159   0.00520   0.0152   1.0000   0.8382
  -1.000  -0.1982   0.01150   0.00520   0.0181   1.0000   0.8733
  -0.750  -0.1751   0.01146   0.00524   0.0193   1.0000   0.9134
  -0.500  -0.1256   0.01154   0.00532   0.0153   1.0000   0.9502
  -0.250  -0.0572   0.01160   0.00535   0.0073   1.0000   0.9784
   0.000   0.0000   0.01154   0.00529   0.0000   1.0000   1.0000
   0.250   0.0573   0.01160   0.00535  -0.0073   0.9783   1.0000
   0.500   0.1256   0.01154   0.00532  -0.0153   0.9502   1.0000
   0.750   0.1751   0.01146   0.00523  -0.0193   0.9134   1.0000
   1.000   0.1983   0.01150   0.00521  -0.0181   0.8733   1.0000
   1.250   0.2142   0.01159   0.00520  -0.0152   0.8382   1.0000
   1.500   0.2304   0.01172   0.00522  -0.0124   0.8049   1.0000
   1.750   0.2480   0.01187   0.00528  -0.0099   0.7723   1.0000
   2.000   0.2674   0.01204   0.00533  -0.0077   0.7402   1.0000
   2.250   0.2883   0.01221   0.00539  -0.0057   0.7078   1.0000
   2.500   0.3103   0.01240   0.00546  -0.0040   0.6749   1.0000
   2.750   0.3332   0.01260   0.00555  -0.0025   0.6414   1.0000
   3.000   0.3568   0.01282   0.00565  -0.0012   0.6059   1.0000
   3.250   0.3808   0.01306   0.00577   0.0000   0.5685   1.0000
   3.500   0.4050   0.01332   0.00590   0.0012   0.5298   1.0000
   3.750   0.4294   0.01362   0.00606   0.0022   0.4890   1.0000
   4.000   0.4540   0.01396   0.00627   0.0031   0.4446   1.0000
   4.250   0.4785   0.01438   0.00650   0.0039   0.3975   1.0000
   4.500   0.5030   0.01488   0.00685   0.0046   0.3453   1.0000
   4.750   0.5270   0.01556   0.00725   0.0052   0.2928   1.0000
   5.000   0.5511   0.01640   0.00785   0.0057   0.2399   1.0000
   5.250   0.5749   0.01741   0.00862   0.0063   0.1962   1.0000
   5.500   0.5989   0.01853   0.00954   0.0068   0.1641   1.0000
   5.750   0.6234   0.01976   0.01067   0.0073   0.1407   1.0000
   6.000   0.6480   0.02096   0.01180   0.0078   0.1231   1.0000
   6.250   0.6730   0.02239   0.01324   0.0084   0.1104   1.0000
   6.500   0.6978   0.02390   0.01481   0.0089   0.0999   1.0000
   6.750   0.7224   0.02571   0.01653   0.0093   0.0924   1.0000
   7.000   0.7471   0.02752   0.01874   0.0099   0.0860   1.0000
   7.250   0.7709   0.02927   0.02049   0.0103   0.0800   1.0000
   7.500   0.7929   0.03225   0.02388   0.0109   0.0772   1.0000
   7.750   0.8128   0.03500   0.02725   0.0116   0.0740   1.0000
   8.000   0.8324   0.03741   0.02995   0.0120   0.0702   1.0000
   8.250   0.8504   0.04049   0.03330   0.0124   0.0685   1.0000
   8.500   0.8624   0.04477   0.03806   0.0128   0.0682   1.0000
   8.750   0.8529   0.05255   0.04684   0.0123   0.0710   1.0000
   9.000   0.8389   0.05995   0.05472   0.0107   0.0736   1.0000
   9.250   0.8251   0.06639   0.06139   0.0086   0.0757   1.0000
   9.500   0.8152   0.07193   0.06703   0.0068   0.0771   1.0000
   9.750   0.8113   0.07711   0.07221   0.0056   0.0780   1.0000
  10.000   0.7120   0.11186   0.10697  -0.0232   0.1468   1.0000
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