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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.44 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3021-il-1000000-n5.txt
Download as CSV file: xf-s3021-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3021-095-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4304   0.08447   0.08286  -0.0284   1.0000   0.0065
  -9.000  -0.4304   0.08089   0.07930  -0.0300   1.0000   0.0066
  -8.750  -0.4321   0.07714   0.07557  -0.0317   1.0000   0.0067
  -8.500  -0.4482   0.07123   0.06971  -0.0345   1.0000   0.0065
  -8.250  -0.4604   0.06535   0.06386  -0.0397   0.9922   0.0065
  -8.000  -0.5121   0.02521   0.02230  -0.0668   0.9528   0.0063
  -7.750  -0.4963   0.02205   0.01871  -0.0663   0.9294   0.0063
  -7.500  -0.4785   0.02026   0.01659  -0.0651   0.9019   0.0064
  -7.250  -0.4584   0.01908   0.01513  -0.0641   0.8771   0.0065
  -7.000  -0.4373   0.01797   0.01377  -0.0632   0.8554   0.0067
  -6.750  -0.4156   0.01675   0.01227  -0.0624   0.8357   0.0067
  -6.500  -0.3921   0.01593   0.01124  -0.0617   0.8181   0.0070
  -6.250  -0.3682   0.01512   0.01023  -0.0611   0.8019   0.0072
  -6.000  -0.3439   0.01428   0.00919  -0.0605   0.7875   0.0074
  -5.750  -0.3190   0.01359   0.00832  -0.0600   0.7735   0.0077
  -5.500  -0.2937   0.01296   0.00753  -0.0595   0.7607   0.0079
  -5.250  -0.2681   0.01240   0.00683  -0.0591   0.7484   0.0081
  -5.000  -0.2423   0.01188   0.00620  -0.0587   0.7368   0.0083
  -4.750  -0.2163   0.01141   0.00561  -0.0583   0.7256   0.0084
  -4.500  -0.1901   0.01097   0.00506  -0.0580   0.7149   0.0085
  -4.250  -0.1637   0.01059   0.00459  -0.0577   0.7048   0.0086
  -4.000  -0.1371   0.01027   0.00419  -0.0574   0.6953   0.0088
  -3.750  -0.1102   0.01004   0.00389  -0.0571   0.6856   0.0089
  -3.500  -0.0841   0.00954   0.00331  -0.0568   0.6767   0.0092
  -3.250  -0.0577   0.00914   0.00281  -0.0564   0.6682   0.0094
  -3.000  -0.0309   0.00881   0.00241  -0.0562   0.6593   0.0098
  -2.750  -0.0038   0.00858   0.00212  -0.0559   0.6510   0.0103
  -2.500   0.0235   0.00842   0.00190  -0.0558   0.6423   0.0108
  -2.250   0.0510   0.00827   0.00170  -0.0556   0.6337   0.0115
  -2.000   0.0784   0.00817   0.00154  -0.0555   0.6253   0.0121
  -1.750   0.1061   0.00808   0.00140  -0.0553   0.6162   0.0127
  -1.500   0.1337   0.00801   0.00129  -0.0552   0.6073   0.0131
  -1.250   0.1613   0.00796   0.00118  -0.0551   0.5977   0.0140
  -1.000   0.1889   0.00788   0.00108  -0.0550   0.5877   0.0179
  -0.750   0.2158   0.00766   0.00099  -0.0548   0.5781   0.0663
  -0.500   0.2426   0.00745   0.00094  -0.0547   0.5683   0.1284
  -0.250   0.2692   0.00720   0.00090  -0.0545   0.5583   0.2116
   0.000   0.2955   0.00692   0.00089  -0.0544   0.5483   0.3092
   0.250   0.3215   0.00664   0.00089  -0.0542   0.5387   0.4206
   0.500   0.3464   0.00624   0.00091  -0.0538   0.5284   0.5742
   0.750   0.3706   0.00588   0.00095  -0.0531   0.5180   0.7130
   1.000   0.3940   0.00563   0.00099  -0.0520   0.5074   0.8187
   1.250   0.4170   0.00547   0.00108  -0.0506   0.4962   0.9229
   1.500   0.4510   0.00555   0.00114  -0.0518   0.4830   0.9624
   1.750   0.4849   0.00566   0.00118  -0.0531   0.4689   0.9762
   2.000   0.5179   0.00578   0.00123  -0.0542   0.4540   0.9850
   2.250   0.5540   0.00590   0.00128  -0.0561   0.4379   0.9904
   2.500   0.5878   0.00605   0.00134  -0.0575   0.4203   0.9949
   2.750   0.6246   0.00621   0.00142  -0.0596   0.4009   0.9989
   3.000   0.6535   0.00636   0.00150  -0.0599   0.3839   1.0000
   3.250   0.6780   0.00653   0.00160  -0.0593   0.3671   1.0000
   3.500   0.7023   0.00671   0.00171  -0.0586   0.3487   1.0000
   3.750   0.7264   0.00692   0.00184  -0.0579   0.3294   1.0000
   4.000   0.7507   0.00712   0.00197  -0.0572   0.3111   1.0000
   4.250   0.7747   0.00735   0.00211  -0.0565   0.2911   1.0000
   4.500   0.7985   0.00760   0.00228  -0.0558   0.2715   1.0000
   4.750   0.8225   0.00785   0.00246  -0.0551   0.2519   1.0000
   5.000   0.8456   0.00819   0.00267  -0.0543   0.2251   1.0000
   5.250   0.8673   0.00866   0.00294  -0.0533   0.1863   1.0000
   5.500   0.8905   0.00902   0.00318  -0.0526   0.1628   1.0000
   5.750   0.9128   0.00947   0.00349  -0.0517   0.1325   1.0000
   6.000   0.9351   0.00994   0.00381  -0.0509   0.1050   1.0000
   6.250   0.9573   0.01042   0.00416  -0.0500   0.0800   1.0000
   6.500   0.9792   0.01092   0.00454  -0.0492   0.0569   1.0000
   6.750   0.9988   0.01166   0.00508  -0.0480   0.0253   1.0000
   7.000   1.0192   0.01233   0.00565  -0.0468   0.0071   1.0000
   7.250   1.0427   0.01267   0.00601  -0.0462   0.0062   1.0000
   7.500   1.0660   0.01303   0.00639  -0.0455   0.0055   1.0000
   7.750   1.0889   0.01342   0.00683  -0.0448   0.0049   1.0000
   8.000   1.1115   0.01383   0.00728  -0.0440   0.0046   1.0000
   8.250   1.1341   0.01421   0.00772  -0.0433   0.0045   1.0000
   8.500   1.1561   0.01464   0.00819  -0.0424   0.0043   1.0000
   8.750   1.1776   0.01509   0.00869  -0.0416   0.0041   1.0000
   9.000   1.1985   0.01559   0.00924  -0.0406   0.0039   1.0000
   9.250   1.2191   0.01607   0.00977  -0.0396   0.0037   1.0000
   9.500   1.2389   0.01661   0.01035  -0.0385   0.0035   1.0000
   9.750   1.2573   0.01722   0.01103  -0.0372   0.0033   1.0000
  10.000   1.2751   0.01784   0.01171  -0.0359   0.0033   1.0000
  10.250   1.2917   0.01851   0.01244  -0.0344   0.0032   1.0000
  10.500   1.3065   0.01924   0.01324  -0.0326   0.0030   1.0000
  10.750   1.3169   0.02004   0.01412  -0.0301   0.0030   1.0000
  11.000   1.3225   0.02103   0.01520  -0.0270   0.0029   1.0000
  11.250   1.3275   0.02210   0.01636  -0.0240   0.0028   1.0000
  11.500   1.3295   0.02341   0.01779  -0.0210   0.0027   1.0000
  11.750   1.3313   0.02483   0.01932  -0.0183   0.0027   1.0000
  12.000   1.3397   0.02591   0.02047  -0.0166   0.0027   1.0000
  12.250   1.3425   0.02747   0.02214  -0.0147   0.0027   1.0000
  12.500   1.3486   0.02889   0.02364  -0.0133   0.0026   1.0000
  12.750   1.3538   0.03047   0.02531  -0.0121   0.0026   1.0000
  13.000   1.3561   0.03242   0.02736  -0.0110   0.0026   1.0000
  13.250   1.3580   0.03454   0.02958  -0.0102   0.0025   1.0000
  13.500   1.3615   0.03660   0.03173  -0.0097   0.0025   1.0000
  13.750   1.3591   0.03939   0.03464  -0.0093   0.0025   1.0000
  14.000   1.3553   0.04249   0.03786  -0.0092   0.0025   1.0000
  14.250   1.3567   0.04513   0.04059  -0.0094   0.0024   1.0000
  14.500   1.3530   0.04845   0.04403  -0.0097   0.0024   1.0000
  14.750   1.3458   0.05239   0.04809  -0.0105   0.0024   1.0000
  15.000   1.3407   0.05621   0.05203  -0.0114   0.0024   1.0000
  15.250   1.3355   0.06021   0.05616  -0.0126   0.0023   1.0000
  15.500   1.3278   0.06478   0.06084  -0.0142   0.0023   1.0000
  15.750   1.3191   0.06971   0.06589  -0.0160   0.0023   1.0000
  16.000   1.3088   0.07507   0.07138  -0.0183   0.0023   1.0000
  16.250   1.3001   0.08043   0.07686  -0.0207   0.0023   1.0000
  16.500   1.2919   0.08587   0.08241  -0.0232   0.0022   1.0000
  16.750   1.2784   0.09241   0.08908  -0.0263   0.0022   1.0000
  17.000   1.2641   0.09929   0.09608  -0.0297   0.0023   1.0000
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