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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 50,000
Max Cl/Cd: 29.06 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e521-il-50000-n5.txt
Download as CSV file: xf-e521-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 521 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7541   0.09960   0.09264  -0.0242   1.0000   0.0513
 -13.500  -0.7768   0.09128   0.08421  -0.0292   1.0000   0.0508
 -13.250  -0.8001   0.08375   0.07652  -0.0335   1.0000   0.0506
 -13.000  -0.8229   0.07711   0.06967  -0.0368   1.0000   0.0505
 -12.750  -0.8428   0.07147   0.06377  -0.0390   1.0000   0.0508
 -12.500  -0.8611   0.06648   0.05848  -0.0403   1.0000   0.0513
 -12.250  -0.8622   0.06335   0.05537  -0.0405   1.0000   0.0534
 -12.000  -0.8654   0.06031   0.05224  -0.0405   1.0000   0.0555
 -11.750  -0.8695   0.05702   0.04872  -0.0402   1.0000   0.0575
 -11.500  -0.8713   0.05373   0.04514  -0.0395   1.0000   0.0599
 -11.250  -0.8728   0.05064   0.04161  -0.0386   1.0000   0.0630
 -11.000  -0.8651   0.04855   0.03956  -0.0379   1.0000   0.0673
 -10.750  -0.8583   0.04632   0.03713  -0.0369   1.0000   0.0723
 -10.500  -0.8452   0.04399   0.03457  -0.0360   1.0000   0.0779
 -10.250  -0.8366   0.04224   0.03278  -0.0349   1.0000   0.0848
 -10.000  -0.8246   0.04041   0.03086  -0.0338   1.0000   0.0929
  -9.750  -0.8116   0.03871   0.02897  -0.0327   1.0000   0.1029
  -9.500  -0.8016   0.03722   0.02750  -0.0314   1.0000   0.1138
  -9.250  -0.7895   0.03575   0.02604  -0.0301   1.0000   0.1262
  -9.000  -0.7790   0.03442   0.02470  -0.0286   1.0000   0.1405
  -8.750  -0.7684   0.03317   0.02343  -0.0269   1.0000   0.1566
  -8.500  -0.7591   0.03201   0.02230  -0.0250   1.0000   0.1739
  -8.250  -0.7500   0.03094   0.02130  -0.0230   1.0000   0.1926
  -8.000  -0.7419   0.02997   0.02035  -0.0208   1.0000   0.2135
  -7.750  -0.7363   0.02909   0.01959  -0.0180   1.0000   0.2337
  -7.500  -0.7337   0.02836   0.01892  -0.0146   1.0000   0.2545
  -7.250  -0.7332   0.02770   0.01835  -0.0107   1.0000   0.2755
  -7.000  -0.7325   0.02709   0.01780  -0.0068   1.0000   0.2974
  -6.750  -0.7311   0.02647   0.01727  -0.0030   1.0000   0.3217
  -6.500  -0.7279   0.02588   0.01674   0.0007   1.0000   0.3484
  -6.250  -0.7230   0.02531   0.01623   0.0041   1.0000   0.3777
  -6.000  -0.7162   0.02479   0.01582   0.0074   1.0000   0.4099
  -5.750  -0.7076   0.02435   0.01550   0.0105   1.0000   0.4447
  -5.500  -0.6966   0.02407   0.01535   0.0135   1.0000   0.4810
  -5.250  -0.6785   0.02398   0.01534   0.0154   0.9980   0.5204
  -5.000  -0.6489   0.02430   0.01572   0.0157   0.9929   0.5601
  -4.750  -0.6204   0.02469   0.01603   0.0162   0.9878   0.5950
  -4.500  -0.5894   0.02522   0.01645   0.0163   0.9828   0.6253
  -4.250  -0.5621   0.02564   0.01671   0.0167   0.9773   0.6521
  -4.000  -0.5323   0.02618   0.01709   0.0170   0.9721   0.6745
  -3.750  -0.5022   0.02660   0.01731   0.0168   0.9671   0.6962
  -3.500  -0.4751   0.02702   0.01758   0.0173   0.9615   0.7143
  -3.250  -0.4445   0.02737   0.01777   0.0170   0.9564   0.7324
  -3.000  -0.4177   0.02760   0.01783   0.0172   0.9509   0.7498
  -2.750  -0.3912   0.02779   0.01790   0.0175   0.9449   0.7659
  -2.500  -0.3551   0.02810   0.01807   0.0162   0.9405   0.7796
  -2.250  -0.3254   0.02832   0.01817   0.0160   0.9348   0.7922
  -2.000  -0.2904   0.02852   0.01827   0.0148   0.9295   0.8040
  -1.750  -0.2496   0.02869   0.01834   0.0123   0.9253   0.8153
  -1.500  -0.2253   0.02873   0.01829   0.0127   0.9180   0.8272
  -1.250  -0.1900   0.02878   0.01826   0.0110   0.9125   0.8386
  -1.000  -0.1476   0.02893   0.01836   0.0082   0.9072   0.8465
  -0.750  -0.1134   0.02896   0.01833   0.0066   0.9005   0.8561
  -0.500  -0.0699   0.02900   0.01833   0.0034   0.8953   0.8643
  -0.250  -0.0374   0.02903   0.01835   0.0022   0.8872   0.8724
   0.000   0.0003   0.02901   0.01831  -0.0001   0.8810   0.8808
   0.250   0.0375   0.02903   0.01835  -0.0022   0.8724   0.8873
   0.500   0.0701   0.02900   0.01833  -0.0034   0.8644   0.8953
   0.750   0.1134   0.02896   0.01833  -0.0066   0.8561   0.9005
   1.000   0.1476   0.02893   0.01835  -0.0082   0.8465   0.9072
   1.250   0.1898   0.02878   0.01827  -0.0109   0.8387   0.9125
   1.500   0.2252   0.02873   0.01829  -0.0127   0.8272   0.9180
   1.750   0.2495   0.02869   0.01833  -0.0123   0.8153   0.9253
   2.000   0.2904   0.02852   0.01827  -0.0148   0.8040   0.9295
   2.250   0.3253   0.02832   0.01817  -0.0160   0.7921   0.9348
   2.500   0.3552   0.02809   0.01807  -0.0162   0.7797   0.9405
   2.750   0.3912   0.02779   0.01790  -0.0175   0.7658   0.9449
   3.000   0.4177   0.02759   0.01783  -0.0172   0.7498   0.9509
   3.250   0.4447   0.02736   0.01777  -0.0171   0.7324   0.9564
   3.500   0.4752   0.02701   0.01758  -0.0174   0.7143   0.9615
   3.750   0.5023   0.02660   0.01731  -0.0168   0.6962   0.9671
   4.000   0.5324   0.02618   0.01709  -0.0170   0.6745   0.9721
   4.250   0.5621   0.02564   0.01671  -0.0168   0.6521   0.9773
   4.500   0.5894   0.02522   0.01645  -0.0163   0.6254   0.9828
   4.750   0.6204   0.02469   0.01603  -0.0162   0.5951   0.9877
   5.000   0.6489   0.02429   0.01571  -0.0157   0.5601   0.9929
   5.250   0.6786   0.02398   0.01534  -0.0154   0.5205   0.9980
   5.500   0.6967   0.02407   0.01534  -0.0135   0.4809   1.0000
   5.750   0.7077   0.02435   0.01550  -0.0105   0.4447   1.0000
   6.000   0.7164   0.02479   0.01582  -0.0074   0.4099   1.0000
   6.250   0.7231   0.02531   0.01623  -0.0041   0.3778   1.0000
   6.500   0.7279   0.02588   0.01674  -0.0007   0.3482   1.0000
   6.750   0.7311   0.02647   0.01726   0.0029   0.3215   1.0000
   7.000   0.7327   0.02708   0.01779   0.0068   0.2975   1.0000
   7.250   0.7332   0.02770   0.01834   0.0107   0.2755   1.0000
   7.500   0.7338   0.02836   0.01892   0.0146   0.2546   1.0000
   7.750   0.7364   0.02909   0.01959   0.0180   0.2337   1.0000
   8.000   0.7419   0.02996   0.02034   0.0208   0.2137   1.0000
   8.250   0.7499   0.03093   0.02130   0.0231   0.1927   1.0000
   8.500   0.7590   0.03201   0.02230   0.0250   0.1740   1.0000
   8.750   0.7683   0.03316   0.02342   0.0269   0.1567   1.0000
   9.000   0.7788   0.03441   0.02468   0.0286   0.1405   1.0000
   9.250   0.7892   0.03574   0.02603   0.0301   0.1261   1.0000
   9.500   0.8015   0.03721   0.02749   0.0314   0.1138   1.0000
   9.750   0.8119   0.03869   0.02896   0.0327   0.1031   1.0000
  10.000   0.8248   0.04039   0.03084   0.0338   0.0930   1.0000
  10.250   0.8366   0.04222   0.03276   0.0349   0.0848   1.0000
  10.500   0.8451   0.04398   0.03455   0.0360   0.0778   1.0000
  10.750   0.8582   0.04632   0.03713   0.0369   0.0722   1.0000
  11.000   0.8651   0.04853   0.03953   0.0379   0.0673   1.0000
  11.250   0.8729   0.05062   0.04159   0.0386   0.0630   1.0000
  11.500   0.8713   0.05372   0.04512   0.0395   0.0598   1.0000
  11.750   0.8696   0.05701   0.04872   0.0402   0.0574   1.0000
  12.000   0.8656   0.06027   0.05218   0.0405   0.0554   1.0000
  12.250   0.8628   0.06326   0.05527   0.0405   0.0533   1.0000
  12.500   0.8620   0.06639   0.05838   0.0403   0.0513   1.0000
  12.750   0.8433   0.07143   0.06374   0.0390   0.0508   1.0000
  13.000   0.8227   0.07717   0.06973   0.0368   0.0505   1.0000
  13.250   0.8006   0.08375   0.07652   0.0335   0.0506   1.0000
  13.500   0.7773   0.09129   0.08421   0.0292   0.0509   1.0000
  13.750   0.7523   0.10006   0.09310   0.0238   0.0512   1.0000
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