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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 50,000
Max Cl/Cd: 23.75 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-50000.txt
Download as CSV file: xf-joukowsk0009-jf-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6406   0.11284   0.10575   0.0390   1.0000   0.3101
  -9.000  -0.6432   0.11001   0.10296   0.0383   1.0000   0.3228
  -8.750  -0.7752   0.07881   0.07200  -0.0018   1.0000   0.1473
  -8.500  -0.7707   0.07322   0.06637  -0.0031   1.0000   0.1462
  -8.250  -0.7715   0.06726   0.06031  -0.0051   1.0000   0.1443
  -8.000  -0.7754   0.06076   0.05358  -0.0077   1.0000   0.1417
  -7.750  -0.7782   0.05397   0.04633  -0.0100   1.0000   0.1391
  -7.500  -0.7718   0.04831   0.04014  -0.0111   1.0000   0.1388
  -7.250  -0.7588   0.04402   0.03532  -0.0114   1.0000   0.1433
  -7.000  -0.7430   0.03997   0.03068  -0.0114   1.0000   0.1491
  -6.750  -0.7210   0.03707   0.02759  -0.0110   1.0000   0.1566
  -6.500  -0.6993   0.03441   0.02465  -0.0105   1.0000   0.1682
  -6.250  -0.6761   0.03181   0.02176  -0.0100   1.0000   0.1811
  -6.000  -0.6524   0.02980   0.01964  -0.0094   1.0000   0.2000
  -5.750  -0.6281   0.02778   0.01753  -0.0087   1.0000   0.2227
  -5.500  -0.6043   0.02618   0.01600  -0.0078   1.0000   0.2533
  -5.250  -0.5809   0.02471   0.01459  -0.0068   1.0000   0.2936
  -5.000  -0.5583   0.02351   0.01371  -0.0054   1.0000   0.3405
  -4.750  -0.5363   0.02259   0.01308  -0.0036   1.0000   0.3938
  -4.500  -0.5147   0.02188   0.01262  -0.0015   1.0000   0.4484
  -4.250  -0.4933   0.02134   0.01225   0.0008   1.0000   0.5028
  -4.000  -0.4725   0.02097   0.01209   0.0036   1.0000   0.5515
  -3.750  -0.4521   0.02065   0.01191   0.0066   1.0000   0.5975
  -3.500  -0.4322   0.02035   0.01167   0.0097   1.0000   0.6413
  -3.250  -0.4131   0.02009   0.01150   0.0131   1.0000   0.6820
  -3.000  -0.3942   0.01983   0.01130   0.0167   1.0000   0.7210
  -2.750  -0.3759   0.01951   0.01099   0.0201   1.0000   0.7610
  -2.500  -0.3560   0.01926   0.01075   0.0237   1.0000   0.7980
  -2.250  -0.3333   0.01895   0.01042   0.0264   1.0000   0.8381
  -2.000  -0.2950   0.01874   0.01012   0.0264   1.0000   0.8790
  -1.750  -0.2241   0.01857   0.00971   0.0198   1.0000   0.9209
  -1.500  -0.1262   0.01806   0.00889   0.0067   1.0000   0.9610
  -1.250  -0.0327   0.01701   0.00764  -0.0071   1.0000   0.9996
  -1.000  -0.0194   0.01644   0.00709  -0.0072   1.0000   1.0000
  -0.750  -0.0081   0.01598   0.00667  -0.0066   1.0000   1.0000
  -0.500   0.0010   0.01562   0.00636  -0.0055   1.0000   1.0000
  -0.250   0.0048   0.01537   0.00618  -0.0035   1.0000   1.0000
   0.000   0.0000   0.01528   0.00613   0.0000   1.0000   1.0000
   0.250  -0.0048   0.01537   0.00618   0.0035   1.0000   1.0000
   0.500  -0.0009   0.01562   0.00636   0.0055   1.0000   1.0000
   0.750   0.0081   0.01598   0.00667   0.0066   1.0000   1.0000
   1.000   0.0194   0.01644   0.00709   0.0072   1.0000   1.0000
   1.250   0.0327   0.01701   0.00763   0.0071   0.9996   1.0000
   1.500   0.1262   0.01806   0.00889  -0.0067   0.9610   1.0000
   1.750   0.2241   0.01857   0.00970  -0.0198   0.9210   1.0000
   2.000   0.2950   0.01874   0.01012  -0.0264   0.8791   1.0000
   2.250   0.3333   0.01895   0.01042  -0.0264   0.8381   1.0000
   2.500   0.3560   0.01926   0.01075  -0.0237   0.7979   1.0000
   2.750   0.3760   0.01951   0.01099  -0.0201   0.7609   1.0000
   3.000   0.3943   0.01983   0.01130  -0.0167   0.7210   1.0000
   3.250   0.4132   0.02010   0.01150  -0.0132   0.6820   1.0000
   3.500   0.4323   0.02035   0.01167  -0.0097   0.6413   1.0000
   3.750   0.4522   0.02065   0.01191  -0.0066   0.5974   1.0000
   4.000   0.4725   0.02097   0.01208  -0.0036   0.5514   1.0000
   4.250   0.4934   0.02134   0.01225  -0.0008   0.5028   1.0000
   4.500   0.5147   0.02188   0.01262   0.0015   0.4484   1.0000
   4.750   0.5363   0.02259   0.01308   0.0036   0.3937   1.0000
   5.000   0.5583   0.02351   0.01371   0.0054   0.3404   1.0000
   5.250   0.5809   0.02471   0.01459   0.0068   0.2936   1.0000
   5.500   0.6044   0.02618   0.01601   0.0078   0.2533   1.0000
   5.750   0.6281   0.02779   0.01753   0.0087   0.2227   1.0000
   6.000   0.6523   0.02980   0.01963   0.0094   0.2000   1.0000
   6.250   0.6761   0.03181   0.02176   0.0100   0.1811   1.0000
   6.500   0.6993   0.03441   0.02465   0.0105   0.1682   1.0000
   6.750   0.7210   0.03706   0.02758   0.0110   0.1565   1.0000
   7.000   0.7430   0.03997   0.03067   0.0114   0.1491   1.0000
   7.250   0.7588   0.04402   0.03532   0.0114   0.1432   1.0000
   7.500   0.7717   0.04830   0.04014   0.0111   0.1388   1.0000
   7.750   0.7781   0.05396   0.04633   0.0100   0.1390   1.0000
   8.000   0.7752   0.06079   0.05361   0.0076   0.1416   1.0000
   8.250   0.7717   0.06726   0.06032   0.0051   0.1444   1.0000
   8.500   0.7708   0.07324   0.06640   0.0031   0.1462   1.0000
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