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S6062 8% (s6062-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S6062 8% (s6062-il)
Reynolds number: 500,000
Max Cl/Cd: 68.39 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6062-il-500000-n5.txt
Download as CSV file: xf-s6062-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6062 8%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5362   0.08635   0.08412  -0.0099   1.0000   0.0061
  -8.750  -0.5390   0.08169   0.07950  -0.0125   1.0000   0.0059
  -8.500  -0.5432   0.07673   0.07457  -0.0156   1.0000   0.0058
  -8.250  -0.5502   0.07152   0.06940  -0.0194   1.0000   0.0059
  -8.000  -0.5577   0.06530   0.06320  -0.0260   1.0000   0.0058
  -7.750  -0.5600   0.05791   0.05573  -0.0320   1.0000   0.0057
  -7.500  -0.5586   0.05071   0.04837  -0.0358   1.0000   0.0057
  -7.250  -0.5531   0.04411   0.04154  -0.0376   1.0000   0.0059
  -7.000  -0.5449   0.03801   0.03515  -0.0381   1.0000   0.0061
  -6.750  -0.5353   0.03293   0.02971  -0.0378   1.0000   0.0062
  -6.500  -0.5219   0.02815   0.02448  -0.0376   0.9969   0.0060
  -6.250  -0.4958   0.02370   0.01949  -0.0391   0.9869   0.0059
  -6.000  -0.4677   0.02052   0.01583  -0.0401   0.9784   0.0058
  -5.500  -0.4101   0.01638   0.01097  -0.0412   0.9616   0.0057
  -5.250  -0.3823   0.01499   0.00934  -0.0413   0.9528   0.0058
  -5.000  -0.3554   0.01386   0.00800  -0.0410   0.9436   0.0059
  -4.750  -0.3300   0.01294   0.00692  -0.0405   0.9333   0.0061
  -4.500  -0.3048   0.01219   0.00605  -0.0399   0.9233   0.0063
  -4.250  -0.2795   0.01161   0.00536  -0.0392   0.9136   0.0065
  -4.000  -0.2547   0.01084   0.00447  -0.0386   0.9034   0.0069
  -3.750  -0.2294   0.01021   0.00372  -0.0380   0.8931   0.0076
  -3.500  -0.2034   0.00983   0.00325  -0.0376   0.8831   0.0088
  -3.250  -0.1772   0.00955   0.00288  -0.0371   0.8729   0.0099
  -3.000  -0.1504   0.00929   0.00251  -0.0367   0.8622   0.0106
  -2.750  -0.1235   0.00908   0.00222  -0.0364   0.8517   0.0117
  -2.500  -0.0970   0.00875   0.00192  -0.0361   0.8410   0.0327
  -2.250  -0.0710   0.00831   0.00170  -0.0358   0.8301   0.0956
  -2.000  -0.0448   0.00789   0.00153  -0.0357   0.8186   0.1722
  -1.750  -0.0183   0.00758   0.00140  -0.0355   0.8069   0.2382
  -1.500   0.0069   0.00697   0.00127  -0.0354   0.7949   0.3875
  -1.250   0.0325   0.00655   0.00119  -0.0351   0.7824   0.5019
  -1.000   0.0585   0.00628   0.00113  -0.0347   0.7694   0.5814
  -0.750   0.0842   0.00605   0.00109  -0.0342   0.7560   0.6590
  -0.500   0.1097   0.00587   0.00108  -0.0336   0.7420   0.7283
  -0.250   0.1352   0.00576   0.00108  -0.0329   0.7276   0.7806
   0.000   0.1607   0.00571   0.00108  -0.0322   0.7123   0.8209
   0.250   0.1862   0.00569   0.00109  -0.0314   0.6960   0.8551
   0.500   0.2114   0.00570   0.00109  -0.0306   0.6786   0.8859
   0.750   0.2370   0.00573   0.00110  -0.0298   0.6600   0.9144
   1.000   0.2650   0.00578   0.00111  -0.0296   0.6405   0.9392
   1.250   0.2973   0.00586   0.00113  -0.0305   0.6199   0.9606
   1.500   0.3329   0.00595   0.00115  -0.0321   0.5974   0.9788
   1.750   0.3687   0.00607   0.00117  -0.0339   0.5735   0.9928
   2.000   0.4000   0.00621   0.00122  -0.0348   0.5491   1.0000
   2.250   0.4254   0.00638   0.00130  -0.0343   0.5239   1.0000
   2.500   0.4507   0.00659   0.00138  -0.0339   0.4899   1.0000
   2.750   0.4748   0.00699   0.00150  -0.0334   0.4255   1.0000
   3.000   0.4989   0.00746   0.00165  -0.0329   0.3546   1.0000
   3.250   0.5237   0.00788   0.00185  -0.0325   0.2991   1.0000
   3.500   0.5485   0.00834   0.00206  -0.0322   0.2428   1.0000
   3.750   0.5730   0.00885   0.00232  -0.0319   0.1846   1.0000
   4.250   0.6217   0.00999   0.00296  -0.0312   0.0764   1.0000
   4.500   0.6460   0.01059   0.00335  -0.0308   0.0333   1.0000
   4.750   0.6708   0.01111   0.00374  -0.0304   0.0146   1.0000
   5.000   0.6968   0.01142   0.00409  -0.0301   0.0128   1.0000
   5.250   0.7226   0.01177   0.00450  -0.0298   0.0119   1.0000
   5.500   0.7484   0.01212   0.00494  -0.0295   0.0115   1.0000
   5.750   0.7738   0.01253   0.00543  -0.0291   0.0110   1.0000
   6.000   0.7988   0.01301   0.00597  -0.0287   0.0106   1.0000
   6.250   0.8234   0.01354   0.00659  -0.0283   0.0103   1.0000
   6.500   0.8475   0.01416   0.00729  -0.0277   0.0100   1.0000
   6.750   0.8710   0.01483   0.00805  -0.0271   0.0098   1.0000
   7.000   0.8943   0.01551   0.00880  -0.0266   0.0094   1.0000
   7.250   0.9172   0.01623   0.00962  -0.0260   0.0089   1.0000
   7.500   0.9395   0.01704   0.01051  -0.0253   0.0086   1.0000
   7.750   0.9611   0.01795   0.01151  -0.0245   0.0084   1.0000
   8.000   0.9822   0.01894   0.01260  -0.0237   0.0081   1.0000
   8.250   1.0024   0.02009   0.01385  -0.0228   0.0079   1.0000
   8.500   1.0214   0.02148   0.01538  -0.0218   0.0076   1.0000
   8.750   1.0391   0.02323   0.01729  -0.0206   0.0074   1.0000
   9.000   1.0521   0.02633   0.02072  -0.0190   0.0071   1.0000
   9.250   1.0695   0.02789   0.02248  -0.0179   0.0070   1.0000
   9.500   1.0854   0.02959   0.02440  -0.0168   0.0069   1.0000
   9.750   1.0999   0.03125   0.02629  -0.0155   0.0068   1.0000
  10.000   1.1138   0.03268   0.02792  -0.0142   0.0066   1.0000
  10.250   1.1241   0.03452   0.03000  -0.0126   0.0064   1.0000
  10.500   1.1309   0.03655   0.03226  -0.0108   0.0062   1.0000
  10.750   1.1321   0.03875   0.03471  -0.0086   0.0061   1.0000
  11.000   1.1246   0.04124   0.03742  -0.0056   0.0060   1.0000
  11.250   1.1130   0.04421   0.04061  -0.0033   0.0060   1.0000
  11.500   1.1013   0.04745   0.04406  -0.0021   0.0059   1.0000
  11.750   1.0874   0.05136   0.04817  -0.0022   0.0059   1.0000
  12.000   1.0721   0.05599   0.05300  -0.0035   0.0058   1.0000
  12.250   1.0548   0.06164   0.05884  -0.0063   0.0059   1.0000
  12.500   1.0380   0.06808   0.06544  -0.0103   0.0058   1.0000
  12.750   1.0141   0.07702   0.07456  -0.0166   0.0059   1.0000
  13.000   0.9928   0.08671   0.08439  -0.0235   0.0060   1.0000
  13.250   0.9634   0.09986   0.09768  -0.0323   0.0062   1.0000
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