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EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 541 AIRFOIL (e541-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.44 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e541-il-1000000.txt
Download as CSV file: xf-e541-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 541 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4110   0.01703   0.01105  -0.0868   0.7962   0.0049
  -8.000  -0.3900   0.01639   0.01034  -0.0860   0.7935   0.0049
  -7.750  -0.3714   0.01563   0.00951  -0.0848   0.7908   0.0049
  -7.500  -0.3520   0.01517   0.00898  -0.0837   0.7882   0.0048
  -7.250  -0.3348   0.01457   0.00829  -0.0823   0.7855   0.0048
  -7.000  -0.3199   0.01389   0.00756  -0.0804   0.7832   0.0050
  -6.750  -0.3018   0.01345   0.00709  -0.0791   0.7807   0.0051
  -6.500  -0.2846   0.01298   0.00656  -0.0776   0.7782   0.0052
  -6.250  -0.2666   0.01257   0.00612  -0.0762   0.7759   0.0056
  -6.000  -0.2475   0.01225   0.00575  -0.0750   0.7737   0.0058
  -5.750  -0.2282   0.01195   0.00540  -0.0738   0.7714   0.0064
  -5.500  -0.2119   0.01152   0.00495  -0.0720   0.7696   0.0097
  -5.250  -0.1976   0.01105   0.00457  -0.0699   0.7675   0.0257
  -5.000  -0.1846   0.01060   0.00425  -0.0676   0.7652   0.0536
  -4.750  -0.1731   0.01018   0.00396  -0.0650   0.7629   0.0860
  -4.500  -0.1657   0.00984   0.00375  -0.0616   0.7607   0.1211
  -4.250  -0.1574   0.00940   0.00351  -0.0583   0.7586   0.1806
  -4.000  -0.1512   0.00876   0.00323  -0.0549   0.7565   0.2722
  -3.750  -0.1532   0.00761   0.00274  -0.0501   0.7544   0.4382
  -3.500  -0.1533   0.00615   0.00230  -0.0456   0.7521   0.6928
  -3.250  -0.1248   0.00633   0.00250  -0.0458   0.7504   0.7283
  -3.000  -0.0956   0.00652   0.00265  -0.0462   0.7489   0.7402
  -2.750  -0.0662   0.00673   0.00282  -0.0466   0.7473   0.7480
  -2.500  -0.0368   0.00694   0.00300  -0.0470   0.7458   0.7539
  -2.250  -0.0068   0.00734   0.00339  -0.0473   0.7441   0.7610
  -2.000   0.0228   0.00778   0.00385  -0.0475   0.7426   0.7678
  -1.750   0.0528   0.00832   0.00443  -0.0475   0.7412   0.7731
  -1.500   0.0816   0.00841   0.00449  -0.0479   0.7396   0.7758
  -1.250   0.1103   0.00836   0.00441  -0.0485   0.7378   0.7772
  -1.000   0.1392   0.00833   0.00433  -0.0491   0.7361   0.7782
  -0.750   0.1678   0.00824   0.00421  -0.0497   0.7343   0.7791
  -0.500   0.1966   0.00817   0.00412  -0.0502   0.7326   0.7798
  -0.250   0.2255   0.00815   0.00406  -0.0507   0.7305   0.7804
   0.000   0.2542   0.00813   0.00403  -0.0512   0.7281   0.7809
   0.250   0.2821   0.00808   0.00399  -0.0515   0.7254   0.7816
   0.500   0.3103   0.00803   0.00394  -0.0519   0.7223   0.7821
   0.750   0.3389   0.00798   0.00387  -0.0524   0.7192   0.7827
   1.000   0.3678   0.00796   0.00382  -0.0529   0.7164   0.7832
   1.250   0.3963   0.00794   0.00380  -0.0534   0.7136   0.7838
   1.500   0.4241   0.00790   0.00378  -0.0537   0.7105   0.7845
   1.750   0.4523   0.00786   0.00375  -0.0541   0.7071   0.7852
   2.000   0.4807   0.00782   0.00370  -0.0545   0.7037   0.7858
   2.250   0.5094   0.00782   0.00368  -0.0550   0.7002   0.7864
   2.500   0.5368   0.00776   0.00366  -0.0553   0.6965   0.7871
   2.750   0.5646   0.00771   0.00363  -0.0556   0.6923   0.7877
   3.000   0.5927   0.00769   0.00359  -0.0560   0.6880   0.7884
   3.250   0.6201   0.00766   0.00359  -0.0562   0.6832   0.7890
   3.500   0.6473   0.00762   0.00357  -0.0564   0.6778   0.7897
   3.750   0.6748   0.00762   0.00356  -0.0567   0.6724   0.7904
   4.000   0.7017   0.00759   0.00359  -0.0568   0.6656   0.7911
   4.250   0.7282   0.00759   0.00358  -0.0568   0.6581   0.7916
   4.500   0.7545   0.00758   0.00359  -0.0568   0.6481   0.7921
   4.750   0.7797   0.00760   0.00361  -0.0566   0.6350   0.7925
   5.000   0.8027   0.00763   0.00361  -0.0559   0.6169   0.7932
   5.250   0.8228   0.00773   0.00365  -0.0546   0.5892   0.7939
   5.500   0.8360   0.00804   0.00379  -0.0520   0.5453   0.7946
   5.750   0.8460   0.00846   0.00402  -0.0487   0.5003   0.7953
   6.000   0.8544   0.00890   0.00430  -0.0452   0.4597   0.7961
   6.250   0.8557   0.00936   0.00459  -0.0402   0.4169   0.7970
   6.500   0.8566   0.00996   0.00498  -0.0354   0.3714   0.7980
   6.750   0.8620   0.01055   0.00542  -0.0316   0.3343   0.7991
   7.000   0.8680   0.01116   0.00588  -0.0280   0.2981   0.8000
   7.250   0.8744   0.01179   0.00636  -0.0247   0.2644   0.8009
   7.500   0.8820   0.01244   0.00687  -0.0217   0.2341   0.8018
   7.750   0.8917   0.01306   0.00738  -0.0192   0.2080   0.8027
   8.000   0.9017   0.01370   0.00792  -0.0168   0.1831   0.8035
   8.250   0.9117   0.01438   0.00850  -0.0145   0.1596   0.8043
   8.500   0.9221   0.01509   0.00910  -0.0124   0.1381   0.8051
   8.750   0.9333   0.01579   0.00973  -0.0104   0.1177   0.8057
   9.000   0.9431   0.01659   0.01042  -0.0084   0.0971   0.8063
   9.250   0.9541   0.01736   0.01109  -0.0065   0.0786   0.8069
   9.500   0.9660   0.01805   0.01174  -0.0049   0.0652   0.8079
   9.750   0.9770   0.01884   0.01246  -0.0031   0.0517   0.8089
  10.000   0.9885   0.01964   0.01320  -0.0015   0.0402   0.8098
  10.250   1.0003   0.02044   0.01397   0.0000   0.0312   0.8106
  10.500   1.0132   0.02121   0.01473   0.0014   0.0251   0.8114
  10.750   1.0257   0.02202   0.01552   0.0027   0.0210   0.8122
  11.000   1.0396   0.02277   0.01632   0.0038   0.0181   0.8130
  11.250   1.0541   0.02349   0.01708   0.0048   0.0168   0.8138
  11.500   1.0667   0.02435   0.01793   0.0060   0.0143   0.8146
  11.750   1.0789   0.02526   0.01888   0.0072   0.0123   0.8154
  12.000   1.0936   0.02600   0.01967   0.0080   0.0111   0.8162
  12.250   1.1045   0.02703   0.02069   0.0092   0.0089   0.8171
  12.500   1.1159   0.02805   0.02175   0.0103   0.0069   0.8179
  12.750   1.1240   0.02933   0.02304   0.0116   0.0046   0.8186
  13.000   1.1344   0.03047   0.02423   0.0127   0.0041   0.8194
  13.250   1.1404   0.03199   0.02581   0.0141   0.0032   0.8200
  13.500   1.1459   0.03360   0.02752   0.0154   0.0030   0.8206
  13.750   1.1542   0.03498   0.02898   0.0164   0.0029   0.8216
  14.000   1.1632   0.03633   0.03041   0.0173   0.0026   0.8226
  14.250   1.1698   0.03791   0.03210   0.0182   0.0025   0.8237
  14.500   1.1759   0.03961   0.03388   0.0191   0.0024   0.8247
  14.750   1.1817   0.04136   0.03572   0.0199   0.0023   0.8256
  15.000   1.1853   0.04338   0.03784   0.0207   0.0023   0.8266
  15.250   1.1887   0.04548   0.04004   0.0214   0.0022   0.8275
  15.500   1.1918   0.04766   0.04231   0.0219   0.0021   0.8284
  15.750   1.1932   0.05012   0.04487   0.0223   0.0020   0.8293
  16.000   1.1935   0.05276   0.04762   0.0226   0.0020   0.8302
  16.250   1.1932   0.05557   0.05054   0.0228   0.0020   0.8310
  16.500   1.1911   0.05869   0.05378   0.0227   0.0019   0.8319
  16.750   1.1868   0.06221   0.05742   0.0224   0.0019   0.8326
  17.000   1.1787   0.06635   0.06169   0.0219   0.0018   0.8333
  17.250   1.1756   0.07002   0.06547   0.0210   0.0018   0.8340
  17.500   1.1617   0.07535   0.07096   0.0198   0.0018   0.8345
  17.750   1.1521   0.08029   0.07604   0.0182   0.0018   0.8353
  18.000   1.1442   0.08514   0.08103   0.0164   0.0017   0.8362
  18.250   1.1335   0.09063   0.08666   0.0141   0.0018   0.8370
  18.500   1.1268   0.09565   0.09180   0.0118   0.0017   0.8378
  18.750   1.1144   0.10179   0.09808   0.0090   0.0017   0.8384
  19.000   1.1018   0.10812   0.10456   0.0058   0.0017   0.8390
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