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NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr)
Reynolds number: 200,000
Max Cl/Cd: 76.09 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s806a-nr-200000.txt
Download as CSV file: xf-s806a-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S806A Airfoil                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2613   0.09042   0.08679  -0.0549   0.8879   0.0285
  -7.000  -0.2553   0.08680   0.08320  -0.0607   0.8840   0.0291
  -6.750  -0.2514   0.08302   0.07940  -0.0676   0.8796   0.0294
  -6.500  -0.2458   0.07974   0.07603  -0.0726   0.8755   0.0296
  -6.250  -0.2384   0.07724   0.07337  -0.0763   0.8715   0.0299
  -3.250  -0.0712   0.02743   0.02142  -0.0742   0.8351   0.1871
  -2.750   0.0074   0.02037   0.01213  -0.0700   0.8302   0.0362
  -2.500   0.0345   0.01942   0.01114  -0.0697   0.8276   0.0344
  -2.250   0.0613   0.01869   0.01038  -0.0695   0.8249   0.0333
  -2.000   0.0881   0.01817   0.00983  -0.0695   0.8222   0.0337
  -1.750   0.1156   0.01781   0.00938  -0.0696   0.8196   0.0354
  -1.500   0.1432   0.01746   0.00899  -0.0695   0.8170   0.0460
  -1.250   0.1375   0.01496   0.00958  -0.0616   0.8141   0.8617
  -1.000   0.2384   0.01546   0.01009  -0.0712   0.8156   0.9896
  -0.750   0.2820   0.01554   0.01007  -0.0750   0.8136   0.9967
  -0.500   0.3152   0.01564   0.01009  -0.0767   0.8112   1.0000
  -0.250   0.3363   0.01578   0.01018  -0.0759   0.8076   1.0000
   0.000   0.3555   0.01630   0.01064  -0.0748   0.8026   1.0000
   0.250   0.3760   0.01694   0.01127  -0.0745   0.7990   1.0000
   0.500   0.3982   0.01703   0.01124  -0.0743   0.7972   1.0000
   0.750   0.4205   0.01720   0.01146  -0.0742   0.7948   1.0000
   1.000   0.4419   0.01736   0.01161  -0.0738   0.7914   1.0000
   1.250   0.4624   0.01750   0.01174  -0.0731   0.7867   1.0000
   1.500   0.4819   0.01773   0.01196  -0.0723   0.7822   1.0000
   1.750   0.5012   0.01794   0.01217  -0.0713   0.7777   1.0000
   2.000   0.5213   0.01801   0.01224  -0.0701   0.7728   1.0000
   2.250   0.5423   0.01803   0.01226  -0.0688   0.7681   1.0000
   2.500   0.5655   0.01799   0.01220  -0.0678   0.7637   1.0000
   2.750   0.5902   0.01781   0.01202  -0.0667   0.7592   1.0000
   3.000   0.6150   0.01789   0.01209  -0.0657   0.7543   1.0000
   3.250   0.6380   0.01845   0.01267  -0.0651   0.7479   1.0000
   3.500   0.6655   0.01807   0.01234  -0.0652   0.7412   1.0000
   3.750   0.6929   0.01769   0.01201  -0.0649   0.7324   1.0000
   4.000   0.7206   0.01723   0.01158  -0.0643   0.7242   1.0000
   4.250   0.7504   0.01658   0.01107  -0.0638   0.7172   1.0000
   4.500   0.7798   0.01580   0.01029  -0.0629   0.7102   1.0000
   4.750   0.8077   0.01541   0.00988  -0.0619   0.7016   1.0000
   5.000   0.8346   0.01510   0.00969  -0.0616   0.6930   1.0000
   5.250   0.8623   0.01453   0.00921  -0.0611   0.6793   1.0000
   5.500   0.8921   0.01280   0.00731  -0.0590   0.6519   1.0000
   5.750   0.9169   0.01205   0.00642  -0.0574   0.5923   1.0000
   6.000   0.9314   0.01264   0.00607  -0.0546   0.4357   1.0000
   6.250   0.9352   0.01473   0.00716  -0.0517   0.2781   1.0000
   6.500   0.9477   0.01603   0.00804  -0.0499   0.2063   1.0000
   6.750   0.9611   0.01717   0.00888  -0.0483   0.1521   1.0000
   7.000   0.9741   0.01827   0.00972  -0.0465   0.1130   1.0000
   7.250   0.9867   0.01934   0.01057  -0.0447   0.0846   1.0000
   7.500   0.9996   0.02033   0.01142  -0.0429   0.0627   1.0000
   7.750   1.0084   0.02153   0.01245  -0.0404   0.0417   1.0000
   8.000   1.0660   0.02194   0.01335  -0.0482   0.0561   1.0000
   8.250   1.0758   0.02321   0.01454  -0.0461   0.0448   1.0000
   8.500   1.0807   0.02475   0.01604  -0.0434   0.0385   1.0000
   8.750   1.0911   0.02604   0.01740  -0.0415   0.0344   1.0000
   9.000   1.1004   0.02756   0.01895  -0.0397   0.0319   1.0000
   9.250   1.1065   0.02962   0.02105  -0.0373   0.0303   1.0000
   9.500   1.1211   0.03131   0.02282  -0.0356   0.0296   1.0000
   9.750   1.1406   0.03278   0.02441  -0.0345   0.0293   1.0000
  10.000   1.1642   0.03445   0.02622  -0.0339   0.0291   1.0000
  10.250   1.1923   0.03652   0.02848  -0.0337   0.0291   1.0000
  10.500   1.2231   0.03944   0.03172  -0.0342   0.0293   1.0000
  10.750   1.2504   0.04355   0.03615  -0.0348   0.0297   1.0000
  11.000   1.2678   0.04639   0.03926  -0.0341   0.0301   1.0000
  11.250   1.2771   0.04771   0.04078  -0.0320   0.0306   1.0000
  11.500   1.2794   0.04937   0.04274  -0.0291   0.0312   1.0000
  11.750   1.2617   0.05448   0.04863  -0.0243   0.0336   1.0000
  12.000   1.2379   0.06016   0.05483  -0.0204   0.0356   1.0000
  12.250   1.2199   0.06482   0.05979  -0.0179   0.0368   1.0000
  12.500   1.2022   0.06948   0.06468  -0.0162   0.0377   1.0000
  12.750   1.1849   0.07447   0.06986  -0.0149   0.0386   1.0000
  13.000   0.9504   0.12009   0.11675  -0.0331   0.0694   1.0000
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