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EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 335 AIRFOIL (e335-il)
Reynolds number: 500,000
Max Cl/Cd: 81.33 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e335-il-500000.txt
Download as CSV file: xf-e335-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 335 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4302   0.08667   0.08475  -0.0092   1.0000   0.0154
  -9.750  -0.4366   0.08096   0.07905  -0.0119   1.0000   0.0154
  -9.500  -0.5070   0.08530   0.08323  -0.0118   1.0000   0.0148
  -9.250  -0.5194   0.07948   0.07740  -0.0164   1.0000   0.0148
  -9.000  -0.5370   0.07414   0.07201  -0.0185   1.0000   0.0149
  -8.250  -0.5881   0.06141   0.05891  -0.0115   1.0000   0.0152
  -8.000  -0.5979   0.05746   0.05475  -0.0079   1.0000   0.0153
  -7.750  -0.6071   0.05319   0.05038  -0.0048   1.0000   0.0155
  -7.500  -0.6050   0.05076   0.04792  -0.0025   1.0000   0.0156
  -7.250  -0.5997   0.04834   0.04542  -0.0004   0.9938   0.0157
  -7.000  -0.5670   0.04520   0.04193  -0.0044   0.8589   0.0163
  -6.750  -0.5613   0.04312   0.03950  -0.0012   0.8073   0.0166
  -6.500  -0.5533   0.04075   0.03683   0.0018   0.7741   0.0172
  -6.000  -0.5387   0.03388   0.02902   0.0098   0.7295   0.0195
  -4.750  -0.4426   0.01911   0.01217   0.0215   0.6468   0.0114
  -4.500  -0.4129   0.01714   0.00989   0.0217   0.6320   0.0108
  -4.250  -0.3840   0.01582   0.00835   0.0219   0.6180   0.0106
  -4.000  -0.3574   0.01497   0.00735   0.0225   0.6045   0.0111
  -3.750  -0.3324   0.01428   0.00654   0.0232   0.5914   0.0114
  -3.500  -0.3077   0.01380   0.00593   0.0241   0.5785   0.0122
  -3.250  -0.2858   0.01307   0.00519   0.0253   0.5665   0.0133
  -3.000  -0.2621   0.01271   0.00476   0.0263   0.5554   0.0143
  -2.750  -0.2388   0.01238   0.00436   0.0272   0.5448   0.0167
  -2.500  -0.2150   0.01202   0.00396   0.0282   0.5340   0.0194
  -2.250  -0.1921   0.01162   0.00352   0.0294   0.5241   0.0257
  -2.000  -0.1732   0.01090   0.00314   0.0312   0.5148   0.1043
  -1.750  -0.1609   0.00983   0.00284   0.0339   0.5066   0.3095
  -1.500  -0.1769   0.00802   0.00243   0.0425   0.5009   0.6557
  -1.250  -0.1547   0.00822   0.00341   0.0453   0.4926   0.8834
  -1.000  -0.0567   0.01055   0.00554   0.0332   0.4783   0.9084
  -0.750   0.0030   0.01142   0.00624   0.0275   0.4676   0.9164
  -0.500   0.0666   0.01213   0.00681   0.0208   0.4573   0.9219
  -0.250   0.1026   0.01252   0.00707   0.0196   0.4495   0.9305
   0.000   0.1448   0.01256   0.00704   0.0167   0.4414   0.9324
   0.250   0.1783   0.01259   0.00695   0.0155   0.4346   0.9343
   0.500   0.2100   0.01258   0.00690   0.0147   0.4275   0.9367
   0.750   0.2348   0.01265   0.00689   0.0152   0.4217   0.9407
   1.000   0.2557   0.01271   0.00690   0.0166   0.4164   0.9449
   1.250   0.2908   0.01262   0.00677   0.0150   0.4102   0.9460
   1.500   0.3243   0.01259   0.00666   0.0136   0.4044   0.9473
   1.750   0.3566   0.01256   0.00660   0.0126   0.3989   0.9488
   2.000   0.3874   0.01254   0.00655   0.0118   0.3937   0.9507
   2.250   0.4154   0.01259   0.00654   0.0117   0.3887   0.9531
   2.500   0.4375   0.01266   0.00661   0.0127   0.3840   0.9562
   2.750   0.4598   0.01271   0.00665   0.0137   0.3794   0.9592
   3.000   0.4929   0.01264   0.00654   0.0125   0.3746   0.9601
   3.250   0.5253   0.01261   0.00649   0.0113   0.3699   0.9613
   3.500   0.5571   0.01255   0.00644   0.0103   0.3648   0.9626
   3.750   0.5865   0.01255   0.00642   0.0098   0.3602   0.9640
   4.000   0.6146   0.01262   0.00646   0.0095   0.3555   0.9656
   4.250   0.6417   0.01262   0.00651   0.0095   0.3510   0.9676
   4.500   0.6654   0.01268   0.00658   0.0101   0.3465   0.9693
   4.750   0.6832   0.01292   0.00679   0.0120   0.3423   0.9721
   5.000   0.7153   0.01282   0.00673   0.0108   0.3375   0.9729
   5.250   0.7454   0.01276   0.00670   0.0101   0.3324   0.9736
   5.500   0.7748   0.01279   0.00672   0.0095   0.3277   0.9745
   5.750   0.8046   0.01280   0.00677   0.0088   0.3225   0.9757
   6.000   0.8330   0.01281   0.00682   0.0084   0.3173   0.9768
   6.250   0.8589   0.01290   0.00691   0.0085   0.3121   0.9778
   6.500   0.8846   0.01295   0.00702   0.0087   0.3070   0.9788
   6.750   0.9106   0.01300   0.00711   0.0088   0.3009   0.9802
   7.000   0.9340   0.01317   0.00727   0.0094   0.2954   0.9814
   7.250   0.9571   0.01322   0.00742   0.0101   0.2895   0.9823
   7.500   0.9772   0.01340   0.00760   0.0114   0.2832   0.9834
   7.750   1.0047   0.01344   0.00771   0.0111   0.2767   0.9843
   8.000   1.0335   0.01348   0.00779   0.0105   0.2692   0.9850
   8.250   1.0599   0.01356   0.00793   0.0104   0.2615   0.9856
   8.500   1.0851   0.01371   0.00809   0.0105   0.2530   0.9861
   8.750   1.1104   0.01383   0.00828   0.0106   0.2442   0.9867
   9.000   1.1350   0.01403   0.00850   0.0107   0.2346   0.9874
   9.250   1.1601   0.01429   0.00877   0.0107   0.2234   0.9884
   9.500   1.1833   0.01455   0.00906   0.0111   0.2109   0.9892
   9.750   1.2045   0.01489   0.00941   0.0118   0.1973   0.9898
  10.000   1.2241   0.01536   0.00984   0.0127   0.1815   0.9905
  10.250   1.2428   0.01585   0.01032   0.0137   0.1655   0.9912
  10.500   1.2608   0.01644   0.01089   0.0147   0.1493   0.9922
  10.750   1.2770   0.01713   0.01155   0.0160   0.1331   0.9934
  11.000   1.2913   0.01788   0.01226   0.0175   0.1185   0.9941
  11.250   1.3080   0.01869   0.01305   0.0184   0.1043   0.9949
  11.500   1.3225   0.01960   0.01394   0.0194   0.0911   0.9958
  11.750   1.3353   0.02055   0.01488   0.0207   0.0798   0.9969
  12.000   1.3475   0.02152   0.01587   0.0220   0.0704   0.9982
  12.250   1.3585   0.02263   0.01701   0.0231   0.0617   0.9997
  12.500   1.3461   0.02367   0.01808   0.0285   0.0574   1.0000
  12.750   1.3283   0.02463   0.01913   0.0345   0.0552   1.0000
  13.000   1.3094   0.02625   0.02081   0.0390   0.0524   1.0000
  13.250   1.2907   0.02843   0.02306   0.0423   0.0502   1.0000
  13.500   1.2730   0.03090   0.02561   0.0450   0.0480   1.0000
  13.750   1.2589   0.03326   0.02805   0.0473   0.0456   1.0000
  14.000   1.2412   0.03594   0.03079   0.0496   0.0435   1.0000
  14.250   1.2212   0.03886   0.03377   0.0518   0.0422   1.0000
  14.500   1.2015   0.04207   0.03704   0.0536   0.0412   1.0000
  14.750   1.1856   0.04541   0.04046   0.0544   0.0394   1.0000
  15.000   1.1741   0.04869   0.04382   0.0547   0.0371   1.0000
  15.250   1.1607   0.05243   0.04761   0.0544   0.0354   1.0000
  15.500   1.1444   0.05671   0.05194   0.0538   0.0338   1.0000
  15.750   1.1321   0.06077   0.05607   0.0530   0.0324   1.0000
  16.000   1.1238   0.06451   0.05989   0.0522   0.0304   1.0000
  16.250   1.1133   0.06864   0.06407   0.0511   0.0288   1.0000
  16.500   1.1000   0.07326   0.06873   0.0497   0.0275   1.0000
  16.750   1.0899   0.07758   0.07313   0.0485   0.0263   1.0000
  17.000   1.0819   0.08167   0.07730   0.0472   0.0250   1.0000
  17.250   1.0752   0.08565   0.08132   0.0459   0.0234   1.0000
  17.500   1.0639   0.09038   0.08611   0.0443   0.0228   1.0000
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