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EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 50,000
Max Cl/Cd: 30.92 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ste87391-il-50000-n5.txt
Download as CSV file: xf-ste87391-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4951   0.11345   0.10692  -0.0394   1.0019   0.0517
  -9.750  -0.5088   0.10815   0.10170  -0.0404   1.0019   0.0515
  -9.500  -0.5256   0.10232   0.09595  -0.0417   1.0019   0.0512
  -9.250  -0.5480   0.09548   0.08919  -0.0436   1.0019   0.0505
  -9.000  -0.5845   0.08684   0.08059  -0.0469   1.0019   0.0489
  -8.750  -0.6638   0.07462   0.06813  -0.0521   1.0019   0.0455
  -8.500  -0.6820   0.06918   0.06242  -0.0531   1.0019   0.0454
  -8.250  -0.6869   0.06503   0.05804  -0.0535   1.0019   0.0459
  -8.000  -0.6849   0.06145   0.05423  -0.0537   1.0019   0.0469
  -7.750  -0.6788   0.05793   0.05042  -0.0542   1.0019   0.0480
  -7.500  -0.6687   0.05432   0.04640  -0.0548   1.0019   0.0493
  -7.250  -0.6545   0.05089   0.04248  -0.0555   1.0019   0.0503
  -7.000  -0.6367   0.04788   0.03901  -0.0560   1.0019   0.0512
  -6.750  -0.6168   0.04536   0.03606  -0.0562   1.0019   0.0523
  -6.500  -0.5934   0.04330   0.03358  -0.0566   1.0013   0.0536
  -6.250  -0.5633   0.04160   0.03154  -0.0579   0.9985   0.0555
  -5.750  -0.5037   0.03919   0.02882  -0.0610   0.9927   0.0642
  -5.500  -0.4729   0.03811   0.02755  -0.0623   0.9896   0.0688
  -5.250  -0.4405   0.03719   0.02654  -0.0640   0.9869   0.0753
  -5.000  -0.4081   0.03623   0.02556  -0.0658   0.9839   0.0873
  -4.750  -0.3763   0.03520   0.02491  -0.0678   0.9805   0.1265
  -4.500  -0.3425   0.03506   0.02486  -0.0700   0.9769   0.2002
  -4.250  -0.3056   0.03549   0.02531  -0.0732   0.9735   0.2634
  -4.000  -0.2771   0.03566   0.02554  -0.0748   0.9684   0.3139
  -3.750  -0.2461   0.03571   0.02545  -0.0759   0.9644   0.3368
  -3.500  -0.2117   0.03585   0.02545  -0.0776   0.9611   0.3543
  -3.250  -0.1859   0.03570   0.02521  -0.0777   0.9558   0.3706
  -3.000  -0.1549   0.03573   0.02517  -0.0789   0.9513   0.3894
  -2.750  -0.1195   0.03590   0.02529  -0.0808   0.9477   0.4137
  -2.500  -0.0940   0.03577   0.02524  -0.0809   0.9419   0.4399
  -2.250  -0.0633   0.03580   0.02542  -0.0820   0.9371   0.4777
  -2.000  -0.0317   0.03599   0.02591  -0.0827   0.9333   0.5360
  -1.750  -0.0206   0.03600   0.02631  -0.0788   0.9257   0.5975
  -1.500  -0.0037   0.03657   0.02709  -0.0752   0.9203   0.6727
  -1.250   0.0151   0.03695   0.02735  -0.0735   0.9124   0.7389
  -1.000   0.0429   0.03754   0.02775  -0.0732   0.9070   0.7853
  -0.750   0.0568   0.03771   0.02784  -0.0703   0.8987   0.8164
  -0.500   0.0797   0.03798   0.02799  -0.0688   0.8930   0.8466
  -0.250   0.0920   0.03794   0.02787  -0.0657   0.8841   0.8724
   0.000   0.1159   0.03797   0.02780  -0.0644   0.8785   0.8998
   0.250   0.1280   0.03771   0.02750  -0.0615   0.8688   0.9246
   0.500   0.1561   0.03761   0.02732  -0.0616   0.8616   0.9536
   0.750   0.1883   0.03731   0.02697  -0.0630   0.8519   0.9981
   1.000   0.2143   0.03750   0.02705  -0.0637   0.8423   0.9981
   1.250   0.2545   0.03777   0.02719  -0.0666   0.8366   0.9981
   1.500   0.2790   0.03792   0.02727  -0.0670   0.8258   0.9981
   2.000   0.3472   0.03817   0.02738  -0.0705   0.8094   0.9981
   2.250   0.3728   0.03827   0.02745  -0.0709   0.7979   0.9981
   2.500   0.4006   0.03835   0.02750  -0.0715   0.7866   0.9981
   2.750   0.4317   0.03836   0.02749  -0.0725   0.7762   0.9981
   3.000   0.4696   0.03816   0.02727  -0.0744   0.7677   0.9981
   3.250   0.4967   0.03814   0.02727  -0.0746   0.7549   0.9981
   3.500   0.5248   0.03808   0.02723  -0.0750   0.7421   0.9981
   3.750   0.5544   0.03795   0.02712  -0.0755   0.7295   0.9981
   4.000   0.5859   0.03771   0.02692  -0.0761   0.7175   0.9981
   4.250   0.6246   0.03706   0.02631  -0.0774   0.7083   0.9981
   4.500   0.6526   0.03684   0.02614  -0.0774   0.6944   0.9981
   4.750   0.6810   0.03656   0.02595  -0.0774   0.6804   0.9981
   5.000   0.7099   0.03624   0.02569  -0.0773   0.6663   0.9981
   5.250   0.7396   0.03588   0.02540  -0.0773   0.6519   0.9981
   5.500   0.7701   0.03547   0.02509  -0.0774   0.6369   0.9981
   6.000   0.8342   0.03452   0.02426  -0.0777   0.6046   0.9981
   6.250   0.8692   0.03391   0.02371  -0.0781   0.5872   0.9981
   6.500   0.8967   0.03387   0.02370  -0.0779   0.5655   0.9981
   6.750   0.9301   0.03351   0.02334  -0.0782   0.5447   0.9981
   7.000   0.9615   0.03338   0.02318  -0.0784   0.5227   0.9981
   7.250   0.9897   0.03353   0.02333  -0.0783   0.5001   0.9981
   7.500   1.0192   0.03369   0.02342  -0.0784   0.4791   0.9981
   7.750   1.0426   0.03426   0.02399  -0.0780   0.4583   0.9981
   8.000   1.0674   0.03482   0.02454  -0.0778   0.4395   0.9981
   8.250   1.0922   0.03544   0.02517  -0.0775   0.4222   0.9981
   8.500   1.1166   0.03613   0.02588  -0.0774   0.4064   0.9981
   8.750   1.1407   0.03689   0.02669  -0.0772   0.3918   0.9981
   9.000   1.1646   0.03771   0.02758  -0.0770   0.3784   0.9981
   9.250   1.1890   0.03854   0.02853  -0.0770   0.3660   0.9981
   9.500   1.2153   0.03933   0.02940  -0.0771   0.3545   0.9981
   9.750   1.2413   0.04016   0.03034  -0.0772   0.3438   0.9981
  10.000   1.2602   0.04130   0.03167  -0.0766   0.3334   0.9981
  10.250   1.2832   0.04228   0.03280  -0.0763   0.3235   0.9981
  10.500   1.3050   0.04329   0.03395  -0.0759   0.3139   0.9981
  10.750   1.3177   0.04465   0.03555  -0.0745   0.3044   0.9981
  11.000   1.3370   0.04569   0.03670  -0.0738   0.2949   0.9981
  11.250   1.3461   0.04709   0.03830  -0.0720   0.2851   0.9981
  11.500   1.3530   0.04859   0.04001  -0.0699   0.2756   0.9981
  11.750   1.3649   0.04972   0.04123  -0.0684   0.2655   0.9981
  12.000   1.3633   0.05154   0.04333  -0.0656   0.2558   0.9981
  12.250   1.3623   0.05332   0.04531  -0.0631   0.2458   0.9981
  12.500   1.3633   0.05483   0.04691  -0.0607   0.2353   0.9981
  12.750   1.3553   0.05705   0.04934  -0.0580   0.2250   0.9981
  13.000   1.3455   0.05959   0.05209  -0.0554   0.2149   0.9981
  13.250   1.3377   0.06197   0.05459  -0.0532   0.2043   0.9981
  13.500   1.3282   0.06461   0.05735  -0.0513   0.1935   0.9981
  13.750   1.3123   0.06848   0.06148  -0.0499   0.1832   0.9981
  14.000   1.2977   0.07239   0.06556  -0.0490   0.1720   0.9981
  14.250   1.2836   0.07656   0.06986  -0.0486   0.1603   0.9981
  14.500   1.2685   0.08124   0.07466  -0.0488   0.1479   0.9981
  14.750   1.2532   0.08635   0.07987  -0.0496   0.1352   0.9981
  15.000   1.2376   0.09183   0.08543  -0.0509   0.1225   0.9981
  15.250   1.2225   0.09748   0.09111  -0.0526   0.1106   0.9981
  15.500   1.2067   0.10355   0.09722  -0.0547   0.0993   0.9981
  15.750   1.1921   0.10961   0.10331  -0.0569   0.0897   0.9981
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