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EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 50,000
Max Cl/Cd: 29.94 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e403-il-50000-n5.txt
Download as CSV file: xf-e403-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5073   0.11207   0.10519  -0.0485   1.0000   0.0419
 -10.750  -0.5273   0.10433   0.09750  -0.0516   1.0000   0.0409
 -10.500  -0.5588   0.09603   0.08921  -0.0552   1.0000   0.0398
 -10.250  -0.6134   0.08752   0.08055  -0.0587   1.0000   0.0385
 -10.000  -0.6451   0.08345   0.07632  -0.0584   1.0000   0.0380
  -9.750  -0.6669   0.08028   0.07311  -0.0570   1.0000   0.0379
  -9.500  -0.6909   0.07757   0.07034  -0.0547   1.0000   0.0378
  -9.250  -0.7125   0.07487   0.06756  -0.0525   1.0000   0.0377
  -9.000  -0.7283   0.07170   0.06425  -0.0510   1.0000   0.0375
  -8.750  -0.7399   0.06844   0.06078  -0.0495   1.0000   0.0375
  -8.500  -0.7474   0.06508   0.05717  -0.0482   1.0000   0.0374
  -8.250  -0.7501   0.06171   0.05351  -0.0470   1.0000   0.0374
  -8.000  -0.7482   0.05843   0.04990  -0.0460   1.0000   0.0374
  -7.750  -0.7420   0.05531   0.04640  -0.0452   1.0000   0.0375
  -7.500  -0.7322   0.05240   0.04304  -0.0444   1.0000   0.0379
  -7.250  -0.7196   0.04973   0.04020  -0.0437   1.0000   0.0389
  -7.000  -0.7049   0.04764   0.03795  -0.0430   1.0000   0.0402
  -6.750  -0.6884   0.04571   0.03579  -0.0421   1.0000   0.0416
  -6.500  -0.6706   0.04386   0.03369  -0.0410   1.0000   0.0431
  -6.250  -0.6518   0.04223   0.03183  -0.0395   1.0000   0.0441
  -6.000  -0.6330   0.04091   0.03030  -0.0375   1.0000   0.0453
  -5.750  -0.6145   0.03988   0.02908  -0.0351   1.0000   0.0467
  -5.500  -0.5975   0.03900   0.02811  -0.0324   1.0000   0.0484
  -5.250  -0.5817   0.03806   0.02717  -0.0306   1.0000   0.0514
  -5.000  -0.5651   0.03719   0.02619  -0.0291   1.0000   0.0558
  -4.750  -0.5412   0.03623   0.02516  -0.0294   0.9974   0.0615
  -4.500  -0.5138   0.03518   0.02399  -0.0306   0.9944   0.0705
  -4.250  -0.4856   0.03351   0.02251  -0.0330   0.9912   0.0938
  -4.000  -0.4584   0.02980   0.02136  -0.0375   0.9893   0.3814
  -3.750  -0.4420   0.03296   0.02493  -0.0314   0.9844   0.5767
  -3.500  -0.4291   0.03542   0.02726  -0.0252   0.9789   0.6235
  -3.250  -0.4126   0.03727   0.02891  -0.0203   0.9742   0.6542
  -3.000  -0.3963   0.03821   0.02966  -0.0164   0.9692   0.6735
  -2.750  -0.3739   0.03853   0.02975  -0.0151   0.9644   0.6879
  -2.500  -0.3424   0.03860   0.02948  -0.0169   0.9603   0.6993
  -2.250  -0.3209   0.03856   0.02925  -0.0158   0.9552   0.7058
  -2.000  -0.2894   0.03837   0.02879  -0.0182   0.9503   0.7144
  -1.750  -0.2606   0.03848   0.02871  -0.0188   0.9459   0.7193
  -1.500  -0.2353   0.03828   0.02831  -0.0194   0.9400   0.7253
  -1.250  -0.2032   0.03819   0.02802  -0.0217   0.9348   0.7310
  -1.000  -0.1727   0.03829   0.02794  -0.0229   0.9300   0.7354
  -0.750  -0.1473   0.03812   0.02765  -0.0236   0.9233   0.7403
  -0.500  -0.1109   0.03817   0.02753  -0.0268   0.9182   0.7456
  -0.250  -0.0858   0.03814   0.02741  -0.0270   0.9117   0.7491
   0.000  -0.0565   0.03815   0.02731  -0.0282   0.9052   0.7533
   0.250  -0.0211   0.03826   0.02731  -0.0309   0.8998   0.7579
   0.500   0.0059   0.03821   0.02719  -0.0319   0.8919   0.7619
   0.750   0.0402   0.03834   0.02726  -0.0338   0.8865   0.7655
   1.000   0.0636   0.03829   0.02718  -0.0340   0.8775   0.7694
   1.250   0.1029   0.03844   0.02726  -0.0371   0.8719   0.7737
   1.500   0.1281   0.03843   0.02724  -0.0378   0.8625   0.7773
   1.750   0.1641   0.03850   0.02730  -0.0398   0.8566   0.7808
   2.000   0.1882   0.03849   0.02731  -0.0401   0.8465   0.7847
   2.250   0.2207   0.03854   0.02737  -0.0419   0.8381   0.7886
   2.500   0.2556   0.03855   0.02741  -0.0439   0.8300   0.7923
   2.750   0.2802   0.03853   0.02744  -0.0440   0.8196   0.7957
   3.000   0.3153   0.03846   0.02742  -0.0457   0.8118   0.7997
   3.250   0.3457   0.03844   0.02746  -0.0470   0.8014   0.8036
   3.500   0.3739   0.03845   0.02756  -0.0479   0.7901   0.8074
   3.750   0.4037   0.03830   0.02751  -0.0485   0.7801   0.8110
   4.000   0.4373   0.03810   0.02741  -0.0497   0.7707   0.8150
   4.250   0.4651   0.03808   0.02752  -0.0504   0.7581   0.8192
   4.500   0.4935   0.03799   0.02755  -0.0509   0.7456   0.8230
   4.750   0.5222   0.03776   0.02746  -0.0512   0.7338   0.8270
   5.000   0.5605   0.03719   0.02708  -0.0526   0.7247   0.8313
   5.250   0.5903   0.03699   0.02703  -0.0532   0.7106   0.8358
   5.500   0.6173   0.03665   0.02686  -0.0529   0.6964   0.8399
   5.750   0.6460   0.03621   0.02662  -0.0528   0.6821   0.8444
   6.000   0.6774   0.03570   0.02630  -0.0531   0.6674   0.8492
   6.250   0.7081   0.03512   0.02592  -0.0530   0.6522   0.8539
   6.500   0.7392   0.03443   0.02546  -0.0528   0.6361   0.8591
   6.750   0.7746   0.03365   0.02488  -0.0531   0.6187   0.8643
   7.000   0.8065   0.03298   0.02439  -0.0529   0.5982   0.8696
   7.250   0.8374   0.03241   0.02401  -0.0526   0.5740   0.8754
   7.500   0.8709   0.03189   0.02361  -0.0527   0.5462   0.8814
   7.750   0.8998   0.03152   0.02332  -0.0520   0.5160   0.8877
   8.000   0.9267   0.03153   0.02338  -0.0515   0.4825   0.8946
   8.250   0.9476   0.03177   0.02363  -0.0502   0.4497   0.9019
   8.500   0.9665   0.03228   0.02414  -0.0489   0.4164   0.9103
   8.750   0.9808   0.03293   0.02480  -0.0471   0.3840   0.9201
   9.000   0.9932   0.03375   0.02564  -0.0453   0.3517   0.9319
   9.250   1.0039   0.03473   0.02661  -0.0435   0.3196   0.9488
   9.500   1.0123   0.03580   0.02767  -0.0419   0.2878   1.0000
   9.750   1.0236   0.03746   0.02927  -0.0412   0.2543   1.0000
  10.000   1.0336   0.03932   0.03107  -0.0406   0.2220   1.0000
  10.250   1.0422   0.04138   0.03309  -0.0399   0.1915   1.0000
  10.500   1.0479   0.04372   0.03534  -0.0393   0.1607   1.0000
  10.750   1.0512   0.04634   0.03783  -0.0387   0.1310   1.0000
  11.000   1.0540   0.04917   0.04050  -0.0384   0.1066   1.0000
  11.250   1.0585   0.05206   0.04337  -0.0380   0.0878   1.0000
  11.500   1.0625   0.05508   0.04639  -0.0377   0.0748   1.0000
  11.750   1.0680   0.05808   0.04944  -0.0374   0.0660   1.0000
  12.000   1.0722   0.06114   0.05250  -0.0373   0.0600   1.0000
  12.250   1.0819   0.06392   0.05554  -0.0371   0.0540   1.0000
  12.500   1.0880   0.06689   0.05855  -0.0371   0.0504   1.0000
  12.750   1.1011   0.06962   0.06150  -0.0369   0.0474   1.0000
  13.000   1.1135   0.07255   0.06471  -0.0367   0.0450   1.0000
  13.250   1.1220   0.07576   0.06815  -0.0368   0.0432   1.0000
  13.500   1.1274   0.07915   0.07169  -0.0371   0.0416   1.0000
  13.750   1.1339   0.08250   0.07506  -0.0374   0.0402   1.0000
  14.000   1.1287   0.08732   0.08028  -0.0382   0.0394   1.0000
  14.250   1.1197   0.09268   0.08601  -0.0397   0.0388   1.0000
  14.500   1.1078   0.09865   0.09230  -0.0419   0.0383   1.0000
  14.750   1.0930   0.10533   0.09927  -0.0449   0.0381   1.0000
  15.000   1.0759   0.11282   0.10704  -0.0490   0.0381   1.0000
  15.250   1.0564   0.12135   0.11580  -0.0541   0.0382   1.0000
  15.500   1.0357   0.13094   0.12560  -0.0604   0.0386   1.0000
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