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Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf)
Reynolds number: 50,000
Max Cl/Cd: 17.82 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0015-jf-50000.txt
Download as CSV file: xf-joukowsk0015-jf-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=15%                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5750   0.10333   0.09509   0.0158   1.0000   0.2977
  -9.500  -0.5712   0.09813   0.08985   0.0140   1.0000   0.2951
  -9.250  -0.5770   0.09257   0.08430   0.0117   1.0000   0.2943
  -9.000  -0.5918   0.08624   0.07799   0.0087   1.0000   0.2943
  -8.750  -0.6222   0.07814   0.06996   0.0044   1.0000   0.2949
  -8.500  -0.6288   0.07310   0.06495   0.0029   1.0000   0.3004
  -8.250  -0.6753   0.06324   0.05517  -0.0023   1.0000   0.3033
  -8.000  -0.7427   0.05225   0.04407  -0.0061   1.0000   0.3070
  -7.750  -0.7805   0.04473   0.03614  -0.0071   1.0000   0.3155
  -7.500  -0.7446   0.04531   0.03688  -0.0056   1.0000   0.3281
  -7.250  -0.7229   0.04438   0.03598  -0.0044   1.0000   0.3404
  -7.000  -0.7212   0.04118   0.03258  -0.0041   1.0000   0.3533
  -6.750  -0.7063   0.03964   0.03095  -0.0032   1.0000   0.3677
  -6.500  -0.6752   0.03989   0.03137  -0.0016   1.0000   0.3806
  -6.250  -0.6559   0.03890   0.03039  -0.0003   1.0000   0.3947
  -6.000  -0.6425   0.03730   0.02873   0.0006   1.0000   0.4095
  -5.750  -0.6297   0.03583   0.02718   0.0018   1.0000   0.4253
  -5.500  -0.6059   0.03575   0.02722   0.0036   1.0000   0.4390
  -5.250  -0.5865   0.03541   0.02698   0.0056   1.0000   0.4526
  -5.000  -0.5776   0.03434   0.02591   0.0077   1.0000   0.4667
  -4.750  -0.5738   0.03313   0.02464   0.0100   1.0000   0.4818
  -4.500  -0.5601   0.03318   0.02481   0.0130   1.0000   0.4939
  -4.250  -0.5529   0.03261   0.02427   0.0157   1.0000   0.5068
  -4.000  -0.5480   0.03177   0.02339   0.0180   1.0000   0.5218
  -3.750  -0.5403   0.03118   0.02276   0.0200   1.0000   0.5369
  -3.500  -0.5287   0.03123   0.02292   0.0228   1.0000   0.5491
  -3.250  -0.5194   0.03080   0.02250   0.0247   1.0000   0.5640
  -3.000  -0.5095   0.03032   0.02199   0.0263   1.0000   0.5800
  -2.750  -0.4984   0.02994   0.02159   0.0276   1.0000   0.5969
  -2.500  -0.4822   0.03002   0.02173   0.0290   0.9982   0.6120
  -2.250  -0.4276   0.03033   0.02202   0.0235   0.9795   0.6362
  -2.000  -0.3783   0.03076   0.02248   0.0198   0.9606   0.6572
  -1.750  -0.3281   0.03116   0.02289   0.0162   0.9422   0.6782
  -1.500  -0.2776   0.03152   0.02328   0.0129   0.9243   0.6991
  -1.250  -0.2257   0.03184   0.02360   0.0095   0.9066   0.7198
  -1.000  -0.1726   0.03209   0.02387   0.0062   0.8890   0.7403
  -0.750  -0.1255   0.03225   0.02403   0.0039   0.8711   0.7600
  -0.500  -0.0813   0.03234   0.02412   0.0022   0.8530   0.7791
  -0.250  -0.0400   0.03239   0.02417   0.0010   0.8348   0.7979
   0.000   0.0000   0.03239   0.02418   0.0000   0.8164   0.8164
   0.250   0.0399   0.03239   0.02417  -0.0010   0.7979   0.8348
   0.500   0.0812   0.03233   0.02412  -0.0022   0.7790   0.8530
   0.750   0.1256   0.03225   0.02403  -0.0039   0.7599   0.8711
   1.000   0.1728   0.03209   0.02386  -0.0062   0.7402   0.8890
   1.250   0.2255   0.03183   0.02360  -0.0095   0.7197   0.9066
   1.500   0.2776   0.03152   0.02327  -0.0129   0.6991   0.9243
   1.750   0.3282   0.03115   0.02289  -0.0163   0.6782   0.9422
   2.000   0.3784   0.03075   0.02246  -0.0198   0.6571   0.9607
   2.250   0.4276   0.03034   0.02202  -0.0235   0.6362   0.9795
   2.500   0.4822   0.03002   0.02172  -0.0290   0.6121   0.9982
   2.750   0.4984   0.02994   0.02158  -0.0276   0.5969   1.0000
   3.000   0.5094   0.03031   0.02199  -0.0263   0.5800   1.0000
   3.250   0.5194   0.03079   0.02249  -0.0247   0.5640   1.0000
   3.500   0.5287   0.03122   0.02291  -0.0228   0.5491   1.0000
   3.750   0.5403   0.03117   0.02275  -0.0200   0.5370   1.0000
   4.000   0.5479   0.03177   0.02339  -0.0179   0.5218   1.0000
   4.250   0.5528   0.03262   0.02427  -0.0157   0.5069   1.0000
   4.500   0.5600   0.03317   0.02480  -0.0130   0.4939   1.0000
   4.750   0.5737   0.03313   0.02464  -0.0100   0.4818   1.0000
   5.000   0.5776   0.03435   0.02591  -0.0077   0.4668   1.0000
   5.250   0.5865   0.03541   0.02698  -0.0056   0.4526   1.0000
   5.500   0.6058   0.03576   0.02723  -0.0036   0.4390   1.0000
   5.750   0.6297   0.03583   0.02718  -0.0018   0.4253   1.0000
   6.000   0.6425   0.03730   0.02872  -0.0006   0.4095   1.0000
   6.250   0.6560   0.03889   0.03038   0.0003   0.3947   1.0000
   6.500   0.6752   0.03989   0.03137   0.0015   0.3807   1.0000
   6.750   0.7063   0.03964   0.03095   0.0031   0.3676   1.0000
   7.000   0.7212   0.04119   0.03259   0.0041   0.3533   1.0000
   7.250   0.7230   0.04438   0.03598   0.0044   0.3404   1.0000
   7.500   0.7447   0.04531   0.03688   0.0056   0.3281   1.0000
   7.750   0.7804   0.04475   0.03617   0.0071   0.3155   1.0000
   8.000   0.7431   0.05223   0.04405   0.0061   0.3069   1.0000
   8.250   0.6739   0.06344   0.05537   0.0021   0.3033   1.0000
   8.500   0.6283   0.07324   0.06509  -0.0030   0.3004   1.0000
   8.750   0.7824   0.05816   0.05004   0.0085   0.2782   1.0000
   9.000   0.6972   0.07162   0.06353   0.0029   0.2792   1.0000
   9.250   0.4859   0.11021   0.10196  -0.0287   0.4237   1.0000
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