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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 50,000
Max Cl/Cd: 25.66 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-50000-n5.txt
Download as CSV file: xf-joukowsk0009-jf-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7680   0.08649   0.07946   0.0059   1.0000   0.0583
 -10.000  -0.8509   0.06953   0.06217  -0.0099   1.0000   0.0545
  -9.750  -0.8646   0.06462   0.05708  -0.0114   1.0000   0.0547
  -9.500  -0.8667   0.06054   0.05284  -0.0121   1.0000   0.0555
  -9.250  -0.8664   0.05647   0.04853  -0.0126   1.0000   0.0563
  -9.000  -0.8622   0.05262   0.04439  -0.0128   1.0000   0.0574
  -8.750  -0.8537   0.04922   0.04070  -0.0128   1.0000   0.0593
  -8.500  -0.8434   0.04583   0.03688  -0.0127   1.0000   0.0624
  -8.250  -0.8313   0.04220   0.03258  -0.0125   1.0000   0.0655
  -8.000  -0.8131   0.03947   0.02969  -0.0121   1.0000   0.0683
  -7.750  -0.7933   0.03728   0.02728  -0.0117   1.0000   0.0722
  -7.500  -0.7727   0.03497   0.02446  -0.0112   1.0000   0.0782
  -7.250  -0.7511   0.03312   0.02265  -0.0107   1.0000   0.0835
  -7.000  -0.7281   0.03128   0.02047  -0.0101   1.0000   0.0911
  -6.750  -0.7060   0.02976   0.01899  -0.0096   1.0000   0.0998
  -6.500  -0.6830   0.02820   0.01731  -0.0090   1.0000   0.1098
  -6.250  -0.6601   0.02685   0.01591  -0.0084   1.0000   0.1236
  -6.000  -0.6371   0.02554   0.01461  -0.0079   1.0000   0.1401
  -5.750  -0.6139   0.02432   0.01338  -0.0074   1.0000   0.1624
  -5.500  -0.5908   0.02319   0.01230  -0.0069   1.0000   0.1905
  -5.250  -0.5678   0.02213   0.01143  -0.0065   1.0000   0.2240
  -5.000  -0.5443   0.02123   0.01065  -0.0060   1.0000   0.2647
  -4.750  -0.5206   0.02046   0.01003  -0.0055   1.0000   0.3089
  -4.500  -0.4968   0.01981   0.00949  -0.0049   1.0000   0.3542
  -4.250  -0.4731   0.01926   0.00906  -0.0041   1.0000   0.3987
  -4.000  -0.4495   0.01880   0.00871  -0.0031   1.0000   0.4415
  -3.750  -0.4260   0.01840   0.00841  -0.0020   1.0000   0.4819
  -3.500  -0.4023   0.01804   0.00811  -0.0009   1.0000   0.5211
  -3.250  -0.3788   0.01772   0.00787   0.0004   1.0000   0.5579
  -3.000  -0.3553   0.01742   0.00763   0.0016   1.0000   0.5943
  -2.750  -0.3322   0.01715   0.00744   0.0031   1.0000   0.6279
  -2.500  -0.3094   0.01690   0.00724   0.0046   1.0000   0.6609
  -2.250  -0.2870   0.01666   0.00708   0.0062   1.0000   0.6934
  -2.000  -0.2649   0.01644   0.00693   0.0079   1.0000   0.7255
  -1.750  -0.2433   0.01623   0.00678   0.0096   1.0000   0.7578
  -1.500  -0.2217   0.01603   0.00665   0.0113   1.0000   0.7906
  -1.250  -0.1991   0.01584   0.00655   0.0128   1.0000   0.8238
  -1.000  -0.1731   0.01569   0.00646   0.0136   1.0000   0.8584
  -0.750  -0.1407   0.01556   0.00637   0.0129   1.0000   0.8950
  -0.500  -0.0978   0.01546   0.00629   0.0099   1.0000   0.9307
  -0.250  -0.0479   0.01536   0.00620   0.0051   1.0000   0.9655
   0.000   0.0000   0.01528   0.00613   0.0000   1.0000   1.0000
   0.250   0.0479   0.01537   0.00620  -0.0051   0.9654   1.0000
   0.500   0.0979   0.01546   0.00629  -0.0099   0.9307   1.0000
   0.750   0.1407   0.01556   0.00637  -0.0129   0.8950   1.0000
   1.000   0.1731   0.01568   0.00646  -0.0136   0.8584   1.0000
   1.250   0.1991   0.01584   0.00655  -0.0128   0.8238   1.0000
   1.500   0.2217   0.01603   0.00665  -0.0113   0.7906   1.0000
   1.750   0.2433   0.01623   0.00678  -0.0096   0.7578   1.0000
   2.000   0.2650   0.01644   0.00693  -0.0079   0.7256   1.0000
   2.250   0.2870   0.01666   0.00708  -0.0062   0.6933   1.0000
   2.500   0.3095   0.01690   0.00724  -0.0046   0.6609   1.0000
   2.750   0.3323   0.01715   0.00744  -0.0031   0.6278   1.0000
   3.000   0.3553   0.01742   0.00763  -0.0016   0.5943   1.0000
   3.250   0.3788   0.01772   0.00787  -0.0004   0.5579   1.0000
   3.500   0.4023   0.01804   0.00811   0.0009   0.5211   1.0000
   3.750   0.4260   0.01840   0.00841   0.0020   0.4819   1.0000
   4.000   0.4496   0.01880   0.00871   0.0031   0.4414   1.0000
   4.250   0.4731   0.01926   0.00906   0.0041   0.3987   1.0000
   4.500   0.4968   0.01981   0.00949   0.0049   0.3541   1.0000
   4.750   0.5207   0.02046   0.01003   0.0055   0.3089   1.0000
   5.000   0.5443   0.02123   0.01065   0.0060   0.2647   1.0000
   5.250   0.5678   0.02213   0.01143   0.0065   0.2240   1.0000
   5.500   0.5908   0.02319   0.01230   0.0069   0.1904   1.0000
   5.750   0.6139   0.02432   0.01338   0.0074   0.1624   1.0000
   6.000   0.6371   0.02554   0.01461   0.0079   0.1402   1.0000
   6.250   0.6601   0.02685   0.01591   0.0085   0.1236   1.0000
   6.500   0.6829   0.02820   0.01731   0.0090   0.1098   1.0000
   6.750   0.7059   0.02975   0.01898   0.0096   0.0998   1.0000
   7.000   0.7280   0.03128   0.02046   0.0102   0.0912   1.0000
   7.250   0.7510   0.03312   0.02264   0.0107   0.0835   1.0000
   7.500   0.7726   0.03497   0.02446   0.0112   0.0782   1.0000
   7.750   0.7931   0.03727   0.02727   0.0117   0.0722   1.0000
   8.000   0.8130   0.03947   0.02968   0.0122   0.0683   1.0000
   8.250   0.8311   0.04218   0.03256   0.0125   0.0656   1.0000
   8.500   0.8432   0.04582   0.03687   0.0128   0.0624   1.0000
   8.750   0.8534   0.04922   0.04069   0.0128   0.0594   1.0000
   9.000   0.8620   0.05259   0.04436   0.0128   0.0574   1.0000
   9.250   0.8663   0.05643   0.04849   0.0126   0.0563   1.0000
   9.500   0.8663   0.06054   0.05284   0.0121   0.0555   1.0000
   9.750   0.8637   0.06468   0.05715   0.0114   0.0548   1.0000
  10.000   0.8509   0.06950   0.06213   0.0100   0.0545   1.0000
  10.250   0.7686   0.08643   0.07940  -0.0058   0.0583   1.0000
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