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S2048 (s2048-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 500,000
Max Cl/Cd: 78.13 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2048-il-500000-n5.txt
Download as CSV file: xf-s2048-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5048   0.08094   0.07869  -0.0344   1.0000   0.0062
  -9.250  -0.5169   0.07510   0.07290  -0.0369   1.0000   0.0064
  -9.000  -0.5322   0.06988   0.06776  -0.0392   1.0000   0.0062
  -8.750  -0.5519   0.06539   0.06334  -0.0409   1.0000   0.0061
  -8.500  -0.5788   0.05867   0.05658  -0.0448   1.0000   0.0061
  -8.250  -0.6124   0.03206   0.02887  -0.0596   0.9909   0.0063
  -8.000  -0.5968   0.02545   0.02146  -0.0617   0.9867   0.0067
  -7.750  -0.5729   0.02169   0.01715  -0.0632   0.9844   0.0071
  -7.500  -0.5433   0.02035   0.01562  -0.0647   0.9830   0.0076
  -7.250  -0.5166   0.01957   0.01473  -0.0651   0.9802   0.0080
  -7.000  -0.4893   0.01858   0.01356  -0.0656   0.9772   0.0085
  -6.750  -0.4601   0.01751   0.01229  -0.0664   0.9749   0.0093
  -6.500  -0.4293   0.01662   0.01123  -0.0674   0.9731   0.0103
  -6.250  -0.3970   0.01608   0.01056  -0.0687   0.9716   0.0112
  -6.000  -0.3645   0.01552   0.00986  -0.0699   0.9703   0.0117
  -5.750  -0.3391   0.01396   0.00811  -0.0698   0.9667   0.0124
  -5.500  -0.3126   0.01298   0.00702  -0.0698   0.9627   0.0131
  -5.250  -0.2829   0.01242   0.00641  -0.0705   0.9599   0.0142
  -5.000  -0.2522   0.01188   0.00580  -0.0713   0.9574   0.0152
  -4.750  -0.2240   0.01133   0.00518  -0.0714   0.9539   0.0160
  -4.500  -0.1977   0.01087   0.00466  -0.0712   0.9486   0.0167
  -4.250  -0.1685   0.01046   0.00417  -0.0715   0.9448   0.0174
  -4.000  -0.1390   0.01010   0.00374  -0.0719   0.9413   0.0179
  -3.750  -0.1130   0.00980   0.00338  -0.0715   0.9347   0.0182
  -3.500  -0.0841   0.00947   0.00299  -0.0718   0.9302   0.0195
  -3.250  -0.0566   0.00920   0.00267  -0.0717   0.9242   0.0211
  -3.000  -0.0284   0.00897   0.00241  -0.0717   0.9181   0.0229
  -2.750  -0.0002   0.00875   0.00217  -0.0717   0.9120   0.0280
  -2.500   0.0273   0.00843   0.00197  -0.0717   0.9048   0.0606
  -2.250   0.0551   0.00818   0.00181  -0.0717   0.8976   0.0919
  -2.000   0.0826   0.00787   0.00165  -0.0717   0.8894   0.1410
  -1.750   0.1090   0.00735   0.00148  -0.0717   0.8792   0.2550
  -1.500   0.1353   0.00688   0.00133  -0.0716   0.8669   0.3701
  -1.250   0.1610   0.00643   0.00124  -0.0713   0.8517   0.4955
  -1.000   0.1865   0.00617   0.00124  -0.0708   0.8343   0.5999
  -0.750   0.2126   0.00610   0.00122  -0.0702   0.8164   0.6470
  -0.500   0.2387   0.00605   0.00123  -0.0697   0.7995   0.6868
  -0.250   0.2652   0.00604   0.00123  -0.0692   0.7843   0.7117
   0.000   0.2920   0.00606   0.00123  -0.0689   0.7701   0.7292
   0.250   0.3189   0.00608   0.00123  -0.0686   0.7563   0.7432
   0.500   0.3457   0.00611   0.00124  -0.0683   0.7414   0.7558
   0.750   0.3723   0.00615   0.00126  -0.0679   0.7251   0.7684
   1.000   0.3987   0.00620   0.00130  -0.0675   0.7075   0.7816
   1.250   0.4249   0.00626   0.00133  -0.0671   0.6868   0.7956
   1.500   0.4504   0.00634   0.00138  -0.0665   0.6613   0.8107
   1.750   0.4755   0.00645   0.00143  -0.0658   0.6328   0.8274
   2.000   0.4994   0.00660   0.00152  -0.0649   0.5956   0.8461
   2.250   0.5222   0.00681   0.00162  -0.0637   0.5503   0.8684
   2.500   0.5440   0.00704   0.00174  -0.0624   0.5037   0.8962
   2.750   0.5671   0.00731   0.00188  -0.0613   0.4546   0.9329
   3.000   0.6000   0.00768   0.00206  -0.0627   0.3990   0.9810
   3.250   0.6254   0.00815   0.00226  -0.0625   0.3399   1.0000
   3.500   0.6495   0.00856   0.00246  -0.0620   0.2951   1.0000
   4.000   0.6998   0.00918   0.00288  -0.0612   0.2409   1.0000
   4.250   0.7249   0.00949   0.00309  -0.0608   0.2162   1.0000
   4.500   0.7499   0.00982   0.00332  -0.0604   0.1933   1.0000
   4.750   0.7749   0.01015   0.00356  -0.0600   0.1694   1.0000
   5.000   0.7997   0.01049   0.00382  -0.0596   0.1458   1.0000
   5.250   0.8234   0.01096   0.00414  -0.0591   0.1128   1.0000
   5.500   0.8470   0.01145   0.00453  -0.0585   0.0853   1.0000
   5.750   0.8711   0.01189   0.00490  -0.0579   0.0679   1.0000
   6.000   0.8949   0.01235   0.00529  -0.0574   0.0530   1.0000
   6.250   0.9188   0.01280   0.00569  -0.0568   0.0416   1.0000
   6.500   0.9430   0.01320   0.00609  -0.0563   0.0340   1.0000
   6.750   0.9667   0.01366   0.00653  -0.0557   0.0278   1.0000
   7.000   0.9909   0.01404   0.00695  -0.0552   0.0240   1.0000
   7.250   1.0142   0.01454   0.00746  -0.0545   0.0186   1.0000
   7.500   1.0372   0.01504   0.00796  -0.0539   0.0136   1.0000
   7.750   1.0600   0.01557   0.00852  -0.0532   0.0101   1.0000
   8.000   1.0818   0.01621   0.00919  -0.0523   0.0075   1.0000
   8.250   1.1038   0.01682   0.00987  -0.0514   0.0065   1.0000
   8.500   1.1250   0.01751   0.01062  -0.0505   0.0056   1.0000
   8.750   1.1449   0.01834   0.01156  -0.0493   0.0050   1.0000
   9.000   1.1629   0.01938   0.01276  -0.0478   0.0046   1.0000
   9.250   1.1819   0.02021   0.01372  -0.0466   0.0044   1.0000
   9.500   1.2001   0.02111   0.01474  -0.0453   0.0042   1.0000
   9.750   1.2179   0.02199   0.01574  -0.0439   0.0039   1.0000
  10.000   1.2354   0.02286   0.01671  -0.0426   0.0037   1.0000
  10.250   1.2512   0.02383   0.01781  -0.0410   0.0034   1.0000
  10.500   1.2657   0.02488   0.01898  -0.0393   0.0033   1.0000
  10.750   1.2778   0.02601   0.02026  -0.0372   0.0032   1.0000
  11.000   1.2868   0.02720   0.02158  -0.0347   0.0031   1.0000
  11.250   1.2939   0.02846   0.02301  -0.0321   0.0030   1.0000
  11.500   1.2993   0.02985   0.02455  -0.0294   0.0029   1.0000
  11.750   1.3024   0.03142   0.02628  -0.0267   0.0028   1.0000
  12.000   1.3028   0.03326   0.02829  -0.0240   0.0027   1.0000
  12.250   1.2979   0.03563   0.03086  -0.0212   0.0026   1.0000
  12.500   1.2933   0.03810   0.03352  -0.0190   0.0026   1.0000
  12.750   1.2882   0.04076   0.03637  -0.0172   0.0026   1.0000
  13.000   1.2796   0.04397   0.03978  -0.0160   0.0026   1.0000
  13.250   1.2550   0.04940   0.04550  -0.0156   0.0025   1.0000
  13.500   1.2439   0.05371   0.04999  -0.0162   0.0025   1.0000
  13.750   1.2290   0.05903   0.05551  -0.0179   0.0025   1.0000
  14.000   1.2171   0.06455   0.06120  -0.0205   0.0025   1.0000
  14.250   1.2006   0.07157   0.06841  -0.0245   0.0025   1.0000
  14.500   1.1805   0.08022   0.07725  -0.0299   0.0025   1.0000
  14.750   1.1661   0.08830   0.08548  -0.0350   0.0025   1.0000
  15.000   1.1475   0.09764   0.09496  -0.0408   0.0025   1.0000
  15.250   1.1243   0.10825   0.10571  -0.0470   0.0025   1.0000
  15.500   1.1118   0.11637   0.11392  -0.0516   0.0026   1.0000
  15.750   1.0925   0.12637   0.12403  -0.0573   0.0026   1.0000
  16.000   1.0716   0.13715   0.13492  -0.0632   0.0028   1.0000
  16.250   1.0385   0.15222   0.15012  -0.0714   0.0028   1.0000
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