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EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 331 AIRFOIL (e331-il)
Reynolds number: 50,000
Max Cl/Cd: 17.45 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e331-il-50000.txt
Download as CSV file: xf-e331-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 331 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4800   0.10291   0.09693   0.0034   1.0000   0.2445
  -8.250  -0.4760   0.09933   0.09342   0.0039   1.0000   0.2601
  -8.000  -0.4758   0.09609   0.09027   0.0043   1.0000   0.2760
  -7.750  -0.4459   0.09177   0.08597   0.0077   1.0000   0.3042
  -7.500  -0.4668   0.08966   0.08401   0.0075   1.0000   0.3233
  -7.250  -0.4290   0.08577   0.08013   0.0122   1.0000   0.3671
  -7.000  -0.4147   0.08308   0.07749   0.0162   1.0000   0.4153
  -6.750  -0.3871   0.08017   0.07462   0.0209   1.0000   0.4780
  -6.500  -0.3449   0.07669   0.07114   0.0251   1.0000   0.5528
  -5.500  -0.2953   0.06402   0.05878   0.0279   1.0000   0.6431
  -5.250  -0.3627   0.06154   0.05663   0.0274   1.0000   0.5742
  -5.000  -0.4131   0.05750   0.05291   0.0254   1.0000   0.5202
  -4.750  -0.4571   0.05425   0.04988   0.0246   1.0000   0.4861
  -4.500  -0.4970   0.05264   0.04841   0.0275   1.0000   0.4685
  -4.250  -0.5346   0.05214   0.04793   0.0322   1.0000   0.4660
  -4.000  -0.5153   0.04709   0.04100   0.0161   1.0000   0.2335
  -3.750  -0.4488   0.04294   0.03503   0.0110   0.9855   0.1338
  -3.500  -0.3926   0.03874   0.03024   0.0063   0.9683   0.1152
  -3.250  -0.3369   0.03623   0.02672   0.0028   0.9498   0.1038
  -3.000  -0.2771   0.03332   0.02333  -0.0022   0.9327   0.1039
  -2.750   0.0311   0.02243   0.01548  -0.0391   0.9643   1.0000
  -2.500   0.1117   0.02187   0.01403  -0.0496   0.9337   1.0000
  -2.250   0.1698   0.02156   0.01318  -0.0556   0.9023   1.0000
  -2.000   0.2045   0.02162   0.01285  -0.0570   0.8727   1.0000
  -1.750   0.2287   0.02188   0.01279  -0.0563   0.8478   1.0000
  -1.500   0.2489   0.02224   0.01291  -0.0550   0.8246   1.0000
  -1.250   0.2688   0.02261   0.01306  -0.0536   0.8050   1.0000
  -1.000   0.2886   0.02300   0.01323  -0.0521   0.7873   1.0000
  -0.750   0.3085   0.02342   0.01347  -0.0507   0.7707   1.0000
  -0.500   0.3285   0.02387   0.01376  -0.0495   0.7553   1.0000
  -0.250   0.3497   0.02436   0.01411  -0.0486   0.7404   1.0000
   0.000   0.3702   0.02489   0.01453  -0.0477   0.7262   1.0000
   0.250   0.3909   0.02548   0.01502  -0.0469   0.7129   1.0000
   0.500   0.4113   0.02610   0.01557  -0.0460   0.7004   1.0000
   0.750   0.4316   0.02669   0.01606  -0.0449   0.6891   1.0000
   1.000   0.4520   0.02728   0.01657  -0.0438   0.6782   1.0000
   1.250   0.4720   0.02814   0.01742  -0.0433   0.6666   1.0000
   1.500   0.4917   0.02890   0.01814  -0.0424   0.6563   1.0000
   1.750   0.5117   0.02959   0.01879  -0.0412   0.6468   1.0000
   2.000   0.5301   0.03071   0.01994  -0.0409   0.6360   1.0000
   2.250   0.5494   0.03149   0.02068  -0.0396   0.6273   1.0000
   2.500   0.5671   0.03263   0.02185  -0.0390   0.6174   1.0000
   2.750   0.5835   0.03390   0.02316  -0.0382   0.6081   1.0000
   3.000   0.6024   0.03472   0.02400  -0.0369   0.5997   1.0000
   3.250   0.6145   0.03654   0.02590  -0.0364   0.5901   1.0000
   3.500   0.6350   0.03717   0.02651  -0.0347   0.5828   1.0000
   3.750   0.6411   0.03954   0.02900  -0.0343   0.5729   1.0000
   4.000   0.6640   0.03997   0.02940  -0.0324   0.5664   1.0000
   4.250   0.6606   0.04314   0.03275  -0.0319   0.5566   1.0000
   4.500   0.6809   0.04390   0.03351  -0.0301   0.5496   1.0000
   4.750   0.6686   0.04758   0.03729  -0.0289   0.5410   1.0000
   5.000   0.6921   0.04816   0.03790  -0.0272   0.5340   1.0000
   5.250   0.6607   0.05295   0.04274  -0.0253   0.5269   1.0000
   5.500   0.7005   0.05251   0.04235  -0.0238   0.5192   1.0000
   5.750   0.6473   0.05846   0.04826  -0.0211   0.5151   1.0000
   6.000   0.6130   0.06219   0.05193  -0.0173   0.5124   1.0000
   6.250   0.5919   0.06527   0.05496  -0.0144   0.5105   1.0000
   6.500   0.6140   0.06674   0.05649  -0.0135   0.5019   1.0000
   6.750   0.5927   0.07013   0.05984  -0.0113   0.5014   1.0000
   7.000   0.5828   0.07337   0.06307  -0.0101   0.5019   1.0000
   7.250   0.5821   0.07664   0.06638  -0.0097   0.5040   1.0000
   7.500   0.4675   0.08513   0.07472  -0.0121   0.6172   1.0000
   7.750   0.4721   0.08716   0.07676  -0.0109   0.6044   1.0000
   8.000   0.4813   0.08955   0.07918  -0.0103   0.5922   1.0000
   8.250   0.4969   0.09231   0.08199  -0.0101   0.5795   1.0000
   8.500   0.5212   0.09576   0.08553  -0.0106   0.5660   1.0000
   8.750   0.5193   0.09717   0.08700  -0.0090   0.5524   1.0000
   9.000   0.5200   0.09911   0.08893  -0.0078   0.5389   1.0000
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