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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 100,000
Max Cl/Cd: 43.06 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e521-il-100000.txt
Download as CSV file: xf-e521-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6497   0.13791   0.13305  -0.0014   1.0000   0.0778
 -13.750  -0.7630   0.09868   0.09387  -0.0252   1.0000   0.0511
 -13.500  -0.7844   0.09056   0.08569  -0.0298   1.0000   0.0502
 -13.250  -0.8104   0.08280   0.07782  -0.0344   1.0000   0.0494
 -13.000  -0.8382   0.07593   0.07079  -0.0380   1.0000   0.0488
 -12.750  -0.8625   0.07021   0.06489  -0.0402   1.0000   0.0482
 -12.500  -0.8864   0.06514   0.05960  -0.0413   1.0000   0.0478
 -12.250  -0.9082   0.06071   0.05494  -0.0412   1.0000   0.0477
 -12.000  -0.9273   0.05689   0.05085  -0.0403   1.0000   0.0481
 -11.750  -0.9434   0.05353   0.04720  -0.0386   1.0000   0.0486
 -11.500  -0.9576   0.05076   0.04413  -0.0361   1.0000   0.0496
 -11.250  -0.9697   0.04844   0.04145  -0.0328   1.0000   0.0506
 -11.000  -0.9758   0.04529   0.03793  -0.0301   1.0000   0.0523
 -10.750  -0.9625   0.04234   0.03498  -0.0295   1.0000   0.0556
 -10.500  -0.9530   0.04012   0.03254  -0.0279   1.0000   0.0591
 -10.250  -0.9480   0.03838   0.03037  -0.0254   1.0000   0.0630
 -10.000  -0.9273   0.03553   0.02755  -0.0253   1.0000   0.0688
  -9.750  -0.9146   0.03397   0.02569  -0.0236   1.0000   0.0750
  -9.500  -0.8938   0.03186   0.02366  -0.0233   1.0000   0.0827
  -9.250  -0.8755   0.03003   0.02169  -0.0222   1.0000   0.0918
  -9.000  -0.8620   0.02888   0.02043  -0.0205   1.0000   0.1020
  -8.750  -0.8462   0.02740   0.01907  -0.0191   1.0000   0.1142
  -8.500  -0.8392   0.02636   0.01812  -0.0163   1.0000   0.1266
  -8.250  -0.8389   0.02557   0.01740  -0.0123   1.0000   0.1386
  -8.000  -0.8392   0.02482   0.01670  -0.0081   1.0000   0.1516
  -7.750  -0.8381   0.02408   0.01597  -0.0041   1.0000   0.1676
  -7.500  -0.8348   0.02331   0.01521  -0.0006   1.0000   0.1866
  -7.250  -0.8302   0.02250   0.01457   0.0027   1.0000   0.2073
  -7.000  -0.8237   0.02172   0.01389   0.0058   1.0000   0.2321
  -6.750  -0.8159   0.02097   0.01327   0.0086   1.0000   0.2603
  -6.500  -0.8071   0.02024   0.01271   0.0112   1.0000   0.2916
  -6.250  -0.7969   0.01954   0.01217   0.0137   1.0000   0.3270
  -6.000  -0.7857   0.01887   0.01171   0.0161   1.0000   0.3661
  -5.750  -0.7734   0.01826   0.01128   0.0184   1.0000   0.4090
  -5.500  -0.7602   0.01773   0.01098   0.0207   1.0000   0.4555
  -5.250  -0.7460   0.01733   0.01082   0.0230   1.0000   0.5047
  -5.000  -0.7308   0.01717   0.01089   0.0255   1.0000   0.5526
  -4.750  -0.7145   0.01730   0.01117   0.0280   1.0000   0.5965
  -4.500  -0.6978   0.01763   0.01156   0.0305   1.0000   0.6346
  -4.250  -0.6779   0.01817   0.01206   0.0325   0.9991   0.6663
  -4.000  -0.6464   0.01905   0.01285   0.0324   0.9943   0.6947
  -3.750  -0.6167   0.01996   0.01370   0.0329   0.9896   0.7158
  -3.500  -0.5866   0.02070   0.01432   0.0329   0.9843   0.7378
  -3.250  -0.5555   0.02154   0.01507   0.0331   0.9796   0.7546
  -3.000  -0.5279   0.02218   0.01563   0.0338   0.9740   0.7707
  -2.750  -0.4937   0.02290   0.01626   0.0333   0.9690   0.7864
  -2.500  -0.4677   0.02337   0.01664   0.0343   0.9632   0.8013
  -2.250  -0.4356   0.02386   0.01705   0.0340   0.9574   0.8154
  -2.000  -0.4005   0.02436   0.01746   0.0330   0.9520   0.8289
  -1.750  -0.3720   0.02465   0.01768   0.0332   0.9453   0.8422
  -1.500  -0.3276   0.02513   0.01808   0.0303   0.9401   0.8547
  -1.250  -0.3028   0.02530   0.01819   0.0308   0.9325   0.8677
  -1.000  -0.2375   0.02593   0.01875   0.0244   0.9280   0.8745
  -0.750  -0.1933   0.02619   0.01896   0.0211   0.9216   0.8845
  -0.500  -0.1341   0.02649   0.01922   0.0152   0.9155   0.8919
  -0.250  -0.0604   0.02669   0.01938   0.0064   0.9113   0.8982
   0.000   0.0001   0.02677   0.01946   0.0000   0.9041   0.9041
   0.250   0.0604   0.02670   0.01938  -0.0064   0.8982   0.9114
   0.500   0.1342   0.02650   0.01922  -0.0152   0.8920   0.9155
   0.750   0.1926   0.02620   0.01897  -0.0210   0.8845   0.9216
   1.000   0.2375   0.02593   0.01875  -0.0244   0.8745   0.9280
   1.250   0.3028   0.02530   0.01819  -0.0309   0.8677   0.9325
   1.500   0.3276   0.02514   0.01808  -0.0303   0.8547   0.9401
   1.750   0.3722   0.02465   0.01768  -0.0332   0.8422   0.9453
   2.000   0.4006   0.02435   0.01745  -0.0330   0.8288   0.9521
   2.250   0.4358   0.02385   0.01704  -0.0340   0.8153   0.9574
   2.500   0.4678   0.02335   0.01662  -0.0342   0.8011   0.9632
   2.750   0.4935   0.02290   0.01626  -0.0333   0.7864   0.9690
   3.000   0.5280   0.02218   0.01563  -0.0339   0.7707   0.9740
   3.250   0.5556   0.02154   0.01506  -0.0331   0.7546   0.9796
   3.500   0.5868   0.02070   0.01432  -0.0329   0.7378   0.9843
   3.750   0.6168   0.01996   0.01370  -0.0329   0.7157   0.9896
   4.000   0.6465   0.01905   0.01286  -0.0324   0.6947   0.9942
   4.250   0.6779   0.01817   0.01206  -0.0325   0.6663   0.9990
   4.500   0.6979   0.01763   0.01156  -0.0305   0.6348   1.0000
   4.750   0.7146   0.01730   0.01117  -0.0280   0.5965   1.0000
   5.000   0.7309   0.01717   0.01089  -0.0255   0.5527   1.0000
   5.250   0.7462   0.01733   0.01082  -0.0231   0.5045   1.0000
   5.500   0.7605   0.01773   0.01099  -0.0208   0.4555   1.0000
   5.750   0.7736   0.01826   0.01128  -0.0185   0.4088   1.0000
   6.000   0.7859   0.01887   0.01171  -0.0162   0.3660   1.0000
   6.250   0.7970   0.01954   0.01217  -0.0138   0.3270   1.0000
   6.500   0.8072   0.02024   0.01271  -0.0113   0.2915   1.0000
   6.750   0.8161   0.02097   0.01327  -0.0086   0.2602   1.0000
   7.000   0.8239   0.02172   0.01389  -0.0058   0.2322   1.0000
   7.250   0.8302   0.02249   0.01457  -0.0027   0.2072   1.0000
   7.500   0.8350   0.02331   0.01522   0.0005   0.1866   1.0000
   7.750   0.8383   0.02408   0.01597   0.0041   0.1676   1.0000
   8.000   0.8393   0.02482   0.01670   0.0081   0.1516   1.0000
   8.250   0.8388   0.02555   0.01739   0.0123   0.1385   1.0000
   8.500   0.8392   0.02636   0.01813   0.0163   0.1265   1.0000
   8.750   0.8460   0.02739   0.01906   0.0191   0.1142   1.0000
   9.000   0.8620   0.02888   0.02042   0.0205   0.1021   1.0000
   9.250   0.8752   0.03002   0.02168   0.0223   0.0917   1.0000
   9.500   0.8936   0.03185   0.02365   0.0233   0.0828   1.0000
   9.750   0.9144   0.03394   0.02565   0.0237   0.0750   1.0000
  10.000   0.9272   0.03553   0.02755   0.0253   0.0689   1.0000
  10.250   0.9480   0.03839   0.03037   0.0254   0.0631   1.0000
  10.500   0.9530   0.04014   0.03256   0.0279   0.0592   1.0000
  10.750   0.9623   0.04232   0.03496   0.0295   0.0556   1.0000
  11.000   0.9759   0.04536   0.03799   0.0301   0.0522   1.0000
  11.250   0.9692   0.04834   0.04135   0.0329   0.0505   1.0000
  11.500   0.9574   0.05070   0.04406   0.0361   0.0495   1.0000
  11.750   0.9429   0.05358   0.04725   0.0387   0.0486   1.0000
  12.000   0.9271   0.05690   0.05086   0.0403   0.0481   1.0000
  12.250   0.9087   0.06073   0.05495   0.0412   0.0479   1.0000
  12.500   0.8878   0.06503   0.05948   0.0412   0.0479   1.0000
  12.750   0.8632   0.07017   0.06485   0.0402   0.0482   1.0000
  13.000   0.8381   0.07600   0.07086   0.0380   0.0488   1.0000
  13.250   0.8111   0.08282   0.07783   0.0344   0.0495   1.0000
  13.500   0.7862   0.09042   0.08554   0.0300   0.0504   1.0000
  13.750   0.7612   0.09910   0.09429   0.0248   0.0511   1.0000
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