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EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 547 AIRFOIL (e547-il)
Reynolds number: 500,000
Max Cl/Cd: 90.17 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e547-il-500000.txt
Download as CSV file: xf-e547-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 547 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.2822   0.15269   0.15047  -0.0336   1.0000   0.0167
 -16.250  -0.2807   0.14996   0.14774  -0.0352   1.0000   0.0173
 -10.000  -0.6686   0.03224   0.02742  -0.0633   0.9579   0.0108
  -9.750  -0.6378   0.02846   0.02332  -0.0660   0.9508   0.0103
  -9.500  -0.5982   0.02481   0.01921  -0.0686   0.9460   0.0094
  -9.250  -0.5530   0.02263   0.01674  -0.0719   0.9399   0.0091
  -9.000  -0.5072   0.02119   0.01517  -0.0759   0.9293   0.0093
  -8.750  -0.4655   0.02003   0.01387  -0.0793   0.9136   0.0096
  -8.500  -0.4356   0.01913   0.01283  -0.0805   0.8936   0.0099
  -8.250  -0.4157   0.01846   0.01203  -0.0797   0.8740   0.0100
  -8.000  -0.3998   0.01782   0.01126  -0.0782   0.8574   0.0107
  -7.750  -0.3843   0.01727   0.01060  -0.0765   0.8426   0.0111
  -7.500  -0.3756   0.01643   0.00966  -0.0740   0.8290   0.0116
  -7.250  -0.3638   0.01582   0.00897  -0.0718   0.8170   0.0122
  -7.000  -0.3512   0.01528   0.00837  -0.0697   0.8051   0.0134
  -6.750  -0.3380   0.01481   0.00781  -0.0675   0.7945   0.0143
  -6.500  -0.3296   0.01422   0.00716  -0.0646   0.7846   0.0168
  -6.250  -0.3214   0.01378   0.00668  -0.0613   0.7744   0.0203
  -6.000  -0.3097   0.01334   0.00622  -0.0587   0.7653   0.0289
  -5.750  -0.2991   0.01275   0.00574  -0.0560   0.7566   0.0518
  -5.500  -0.2862   0.01220   0.00535  -0.0538   0.7482   0.0870
  -5.250  -0.2727   0.01164   0.00496  -0.0517   0.7404   0.1360
  -5.000  -0.2633   0.01078   0.00450  -0.0491   0.7323   0.2253
  -4.750  -0.2595   0.00947   0.00381  -0.0458   0.7247   0.3787
  -4.500  -0.2544   0.00823   0.00347  -0.0423   0.7170   0.5901
  -4.250  -0.2282   0.00841   0.00362  -0.0419   0.7100   0.6345
  -4.000  -0.2009   0.00865   0.00379  -0.0416   0.7031   0.6546
  -3.750  -0.1734   0.00889   0.00393  -0.0414   0.6961   0.6670
  -3.500  -0.1451   0.00912   0.00412  -0.0413   0.6895   0.6742
  -3.250  -0.1178   0.00932   0.00420  -0.0411   0.6823   0.6829
  -3.000  -0.0892   0.00966   0.00454  -0.0409   0.6761   0.6903
  -2.750  -0.0616   0.00997   0.00481  -0.0406   0.6693   0.6999
  -2.500  -0.0330   0.01054   0.00540  -0.0400   0.6632   0.7088
  -2.250  -0.0056   0.01076   0.00557  -0.0398   0.6569   0.7158
  -2.000   0.0221   0.01077   0.00552  -0.0398   0.6504   0.7175
  -1.750   0.0501   0.01078   0.00545  -0.0399   0.6447   0.7189
  -1.500   0.0779   0.01073   0.00536  -0.0401   0.6386   0.7203
  -1.250   0.1057   0.01071   0.00526  -0.0403   0.6328   0.7218
  -1.000   0.1336   0.01067   0.00517  -0.0406   0.6271   0.7232
  -0.750   0.1614   0.01062   0.00506  -0.0408   0.6211   0.7247
  -0.500   0.1894   0.01061   0.00495  -0.0411   0.6159   0.7263
  -0.250   0.2173   0.01056   0.00486  -0.0414   0.6104   0.7276
   0.000   0.2453   0.01051   0.00476  -0.0417   0.6049   0.7287
   0.250   0.2735   0.01053   0.00468  -0.0421   0.5999   0.7300
   0.500   0.3010   0.01045   0.00461  -0.0423   0.5946   0.7310
   0.750   0.3288   0.01042   0.00456  -0.0425   0.5894   0.7319
   1.000   0.3568   0.01045   0.00452  -0.0427   0.5846   0.7328
   1.250   0.3845   0.01043   0.00452  -0.0429   0.5796   0.7338
   1.500   0.4123   0.01043   0.00451  -0.0432   0.5746   0.7348
   1.750   0.4403   0.01048   0.00450  -0.0434   0.5700   0.7359
   2.000   0.4680   0.01050   0.00453  -0.0436   0.5653   0.7372
   2.250   0.4957   0.01051   0.00455  -0.0439   0.5603   0.7385
   2.500   0.5236   0.01055   0.00455  -0.0441   0.5557   0.7397
   2.750   0.5514   0.01059   0.00458  -0.0444   0.5511   0.7408
   3.000   0.5789   0.01060   0.00461  -0.0446   0.5460   0.7420
   3.250   0.6066   0.01064   0.00462  -0.0449   0.5413   0.7432
   3.500   0.6344   0.01072   0.00467  -0.0452   0.5365   0.7443
   3.750   0.6616   0.01074   0.00472  -0.0453   0.5310   0.7453
   4.000   0.6884   0.01074   0.00472  -0.0454   0.5258   0.7465
   4.250   0.7153   0.01080   0.00479  -0.0454   0.5206   0.7477
   4.500   0.7416   0.01081   0.00487  -0.0454   0.5148   0.7489
   4.750   0.7682   0.01089   0.00494  -0.0454   0.5095   0.7502
   5.000   0.7947   0.01095   0.00504  -0.0454   0.5041   0.7514
   5.250   0.8209   0.01099   0.00514  -0.0453   0.4982   0.7527
   5.500   0.8473   0.01111   0.00522  -0.0453   0.4926   0.7540
   5.750   0.8730   0.01115   0.00534  -0.0452   0.4863   0.7555
   6.000   0.8985   0.01122   0.00543  -0.0450   0.4798   0.7569
   6.250   0.9238   0.01131   0.00555  -0.0448   0.4729   0.7584
   6.500   0.9487   0.01139   0.00565  -0.0445   0.4654   0.7598
   6.750   0.9733   0.01149   0.00579  -0.0442   0.4581   0.7611
   7.000   0.9969   0.01156   0.00590  -0.0437   0.4496   0.7627
   7.250   1.0203   0.01165   0.00606  -0.0431   0.4409   0.7643
   7.500   1.0424   0.01180   0.00622  -0.0423   0.4318   0.7660
   7.750   1.0647   0.01191   0.00640  -0.0415   0.4206   0.7677
   8.000   1.0859   0.01207   0.00659  -0.0406   0.4088   0.7695
   8.250   1.1055   0.01226   0.00680  -0.0394   0.3950   0.7714
   8.500   1.1229   0.01251   0.00704  -0.0378   0.3779   0.7733
   8.750   1.1356   0.01281   0.00730  -0.0353   0.3589   0.7753
   9.000   1.1458   0.01318   0.00762  -0.0325   0.3375   0.7772
   9.250   1.1523   0.01374   0.00810  -0.0291   0.3126   0.7794
   9.500   1.1584   0.01439   0.00867  -0.0258   0.2871   0.7816
   9.750   1.1629   0.01514   0.00934  -0.0225   0.2636   0.7842
  10.000   1.1660   0.01601   0.01013  -0.0192   0.2405   0.7871
  10.250   1.1697   0.01692   0.01097  -0.0162   0.2202   0.7901
  10.500   1.1728   0.01791   0.01190  -0.0133   0.2006   0.7929
  10.750   1.1750   0.01899   0.01295  -0.0105   0.1829   0.7958
  11.000   1.1773   0.02017   0.01410  -0.0080   0.1671   0.7989
  11.250   1.1792   0.02148   0.01537  -0.0056   0.1512   0.8024
  11.500   1.1817   0.02285   0.01671  -0.0036   0.1374   0.8059
  11.750   1.1834   0.02432   0.01816  -0.0016   0.1237   0.8094
  12.000   1.1845   0.02590   0.01975   0.0003   0.1113   0.8133
  12.250   1.1859   0.02756   0.02140   0.0019   0.0996   0.8176
  12.500   1.1886   0.02923   0.02308   0.0032   0.0898   0.8222
  12.750   1.1899   0.03100   0.02489   0.0046   0.0807   0.8270
  13.000   1.1895   0.03299   0.02689   0.0059   0.0722   0.8329
  13.250   1.1906   0.03495   0.02888   0.0069   0.0646   0.8393
  13.500   1.1920   0.03691   0.03090   0.0078   0.0578   0.8470
  13.750   1.1898   0.03925   0.03328   0.0088   0.0513   0.8561
  14.000   1.1918   0.04127   0.03538   0.0095   0.0458   0.8685
  14.250   1.1894   0.04364   0.03787   0.0104   0.0417   0.8891
  14.500   1.2010   0.04614   0.04056   0.0083   0.0365   0.9458
  14.750   1.2013   0.04874   0.04320   0.0082   0.0330   1.0000
  15.000   1.2042   0.05121   0.04571   0.0080   0.0302   1.0000
  15.250   1.2014   0.05433   0.04883   0.0078   0.0272   1.0000
  15.500   1.2065   0.05667   0.05124   0.0074   0.0252   1.0000
  15.750   1.2070   0.05956   0.05417   0.0070   0.0232   1.0000
  16.000   1.2035   0.06298   0.05762   0.0065   0.0214   1.0000
  16.250   1.2062   0.06573   0.06047   0.0060   0.0200   1.0000
  16.500   1.2080   0.06862   0.06338   0.0053   0.0181   1.0000
  16.750   1.2028   0.07249   0.06732   0.0044   0.0171   1.0000
  17.000   1.2054   0.07542   0.07034   0.0036   0.0158   1.0000
  17.250   1.2037   0.07896   0.07396   0.0025   0.0147   1.0000
  17.500   1.2003   0.08282   0.07787   0.0013   0.0138   1.0000
  17.750   1.1960   0.08688   0.08202   0.0000   0.0128   1.0000
  18.000   1.1949   0.09057   0.08580  -0.0013   0.0118   1.0000
  18.250   1.1919   0.09457   0.08988  -0.0028   0.0110   1.0000
  18.500   1.1830   0.09956   0.09494  -0.0048   0.0104   1.0000
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