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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 500,000
Max Cl/Cd: 110.71 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e176-il-500000.txt
Download as CSV file: xf-e176-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3911   0.08480   0.08270  -0.0241   1.0000   0.0183
  -8.000  -0.3894   0.08129   0.07922  -0.0260   1.0000   0.0188
  -7.750  -0.3893   0.07784   0.07582  -0.0278   1.0000   0.0190
  -7.500  -0.3923   0.07393   0.07196  -0.0307   1.0000   0.0198
  -7.250  -0.3863   0.06887   0.06693  -0.0371   1.0000   0.0205
  -7.000  -0.3606   0.06206   0.06006  -0.0482   0.9785   0.0210
  -6.750  -0.3246   0.03828   0.03603  -0.0539   0.8651   0.0216
  -6.500  -0.3213   0.03362   0.03122  -0.0553   0.8466   0.0223
  -6.250  -0.3091   0.03089   0.02836  -0.0559   0.8307   0.0230
  -6.000  -0.2950   0.02768   0.02499  -0.0571   0.8168   0.0239
  -5.750  -0.2822   0.03718   0.03409  -0.0655   0.8393   0.0254
  -5.500  -0.2551   0.03524   0.03167  -0.0655   0.8238   0.0294
  -5.250  -0.2432   0.02810   0.02394  -0.0666   0.8109   0.0311
  -5.000  -0.2208   0.02649   0.02225  -0.0667   0.7986   0.0324
  -4.750  -0.1970   0.02520   0.02079  -0.0666   0.7870   0.0349
  -4.500  -0.1666   0.02659   0.02186  -0.0658   0.7757   0.0402
  -4.250  -0.1451   0.01656   0.01065  -0.0646   0.7684   0.0219
  -4.000  -0.1185   0.01505   0.00894  -0.0641   0.7592   0.0204
  -3.750  -0.0920   0.01348   0.00712  -0.0637   0.7505   0.0199
  -3.500  -0.0653   0.01247   0.00591  -0.0632   0.7427   0.0201
  -3.250  -0.0382   0.01172   0.00505  -0.0630   0.7344   0.0206
  -3.000  -0.0112   0.01117   0.00437  -0.0627   0.7272   0.0210
  -2.750   0.0157   0.01047   0.00359  -0.0624   0.7196   0.0219
  -2.500   0.0428   0.00998   0.00298  -0.0622   0.7131   0.0239
  -2.250   0.0706   0.00965   0.00260  -0.0621   0.7058   0.0254
  -2.000   0.0983   0.00945   0.00228  -0.0619   0.6996   0.0285
  -1.750   0.1259   0.00894   0.00198  -0.0618   0.6929   0.0831
  -1.500   0.1526   0.00848   0.00184  -0.0618   0.6870   0.1912
  -1.250   0.1792   0.00797   0.00178  -0.0619   0.6807   0.3331
  -1.000   0.2052   0.00748   0.00175  -0.0618   0.6747   0.4873
  -0.750   0.2290   0.00690   0.00176  -0.0611   0.6693   0.6806
  -0.500   0.2484   0.00625   0.00181  -0.0585   0.6634   0.9112
  -0.250   0.3017   0.00622   0.00169  -0.0639   0.6578   1.0000
   0.000   0.3287   0.00626   0.00167  -0.0636   0.6518   1.0000
   0.250   0.3556   0.00633   0.00165  -0.0634   0.6461   1.0000
   0.500   0.3827   0.00641   0.00165  -0.0632   0.6408   1.0000
   0.750   0.4100   0.00646   0.00166  -0.0631   0.6349   1.0000
   1.000   0.4372   0.00656   0.00167  -0.0629   0.6296   1.0000
   1.250   0.4647   0.00661   0.00171  -0.0628   0.6237   1.0000
   1.500   0.4921   0.00668   0.00173  -0.0627   0.6179   1.0000
   1.750   0.5195   0.00677   0.00178  -0.0626   0.6122   1.0000
   2.000   0.5469   0.00683   0.00182  -0.0624   0.6052   1.0000
   2.250   0.5743   0.00692   0.00187  -0.0623   0.5988   1.0000
   2.500   0.6018   0.00697   0.00192  -0.0622   0.5911   1.0000
   2.750   0.6291   0.00706   0.00198  -0.0621   0.5839   1.0000
   3.000   0.6565   0.00712   0.00205  -0.0620   0.5758   1.0000
   3.250   0.6839   0.00721   0.00213  -0.0619   0.5681   1.0000
   3.500   0.7112   0.00729   0.00221  -0.0617   0.5600   1.0000
   3.750   0.7386   0.00736   0.00230  -0.0617   0.5511   1.0000
   4.000   0.7658   0.00746   0.00241  -0.0615   0.5419   1.0000
   4.250   0.7929   0.00756   0.00251  -0.0614   0.5314   1.0000
   4.500   0.8201   0.00765   0.00263  -0.0612   0.5202   1.0000
   4.750   0.8471   0.00776   0.00276  -0.0611   0.5077   1.0000
   5.000   0.8733   0.00791   0.00288  -0.0608   0.4864   1.0000
   5.250   0.8990   0.00812   0.00301  -0.0605   0.4525   1.0000
   5.500   0.9237   0.00847   0.00321  -0.0600   0.4094   1.0000
   5.750   0.9460   0.00913   0.00356  -0.0594   0.3385   1.0000
   6.000   0.9667   0.01004   0.00411  -0.0586   0.2620   1.0000
   6.250   0.9870   0.01100   0.00472  -0.0579   0.1928   1.0000
   6.500   1.0055   0.01215   0.00544  -0.0569   0.1169   1.0000
   6.750   1.0218   0.01354   0.00635  -0.0556   0.0425   1.0000
   7.000   1.0405   0.01462   0.00725  -0.0544   0.0153   1.0000
   7.250   1.0629   0.01521   0.00792  -0.0537   0.0133   1.0000
   7.500   1.0839   0.01594   0.00872  -0.0527   0.0120   1.0000
   7.750   1.1015   0.01702   0.00992  -0.0513   0.0110   1.0000
   8.000   1.1206   0.01785   0.01086  -0.0501   0.0107   1.0000
   8.250   1.1377   0.01882   0.01193  -0.0487   0.0104   1.0000
   8.500   1.1530   0.01991   0.01312  -0.0470   0.0102   1.0000
   8.750   1.1666   0.02109   0.01442  -0.0452   0.0101   1.0000
   9.000   1.1787   0.02237   0.01581  -0.0432   0.0101   1.0000
   9.250   1.1895   0.02376   0.01730  -0.0410   0.0100   1.0000
   9.500   1.1996   0.02502   0.01865  -0.0387   0.0098   1.0000
   9.750   1.2096   0.02629   0.02003  -0.0365   0.0096   1.0000
  10.000   1.2198   0.02770   0.02154  -0.0346   0.0094   1.0000
  10.250   1.2304   0.02928   0.02325  -0.0327   0.0093   1.0000
  10.500   1.2416   0.03125   0.02537  -0.0310   0.0093   1.0000
  10.750   1.2517   0.03307   0.02734  -0.0295   0.0091   1.0000
  11.000   1.2614   0.03565   0.03017  -0.0278   0.0094   1.0000
  11.250   1.2671   0.03829   0.03304  -0.0261   0.0094   1.0000
  11.500   1.2675   0.04171   0.03675  -0.0242   0.0097   1.0000
  11.750   1.2625   0.04560   0.04092  -0.0225   0.0101   1.0000
  12.000   1.2517   0.05009   0.04568  -0.0211   0.0105   1.0000
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