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EPPLER 862 STRUT AIRFOIL (e862-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 862 STRUT AIRFOIL (e862-il)
Reynolds number: 200,000
Max Cl/Cd: 20.73 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e862-il-200000.txt
Download as CSV file: xf-e862-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 862 STRUT AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3652   0.11662   0.10999  -0.0071   0.6118   0.2738
 -11.750  -0.4169   0.10650   0.09978  -0.0097   0.6118   0.2862
 -11.500  -0.3763   0.10847   0.10167  -0.0094   0.6038   0.2854
 -11.250  -0.3297   0.11103   0.10423  -0.0090   0.5962   0.2838
 -11.000  -0.3276   0.10789   0.10107  -0.0098   0.5920   0.2885
 -10.750  -0.2997   0.10804   0.10119  -0.0099   0.5859   0.2896
 -10.500  -0.2763   0.10763   0.10072  -0.0102   0.5806   0.2914
 -10.250  -0.2637   0.10592   0.09892  -0.0107   0.5760   0.2946
 -10.000  -0.2902   0.09946   0.09241  -0.0120   0.5746   0.3036
  -9.750  -0.2619   0.09954   0.09252  -0.0122   0.5697   0.3048
  -9.500  -0.2385   0.09905   0.09203  -0.0125   0.5651   0.3066
  -9.250  -0.2319   0.09660   0.08955  -0.0131   0.5618   0.3109
  -9.000  -0.2523   0.09111   0.08400  -0.0141   0.5600   0.3191
  -8.750  -0.2243   0.09122   0.08407  -0.0142   0.5559   0.3203
  -8.500  -0.7223   0.03927   0.03157  -0.0120   0.5755   0.3810
  -8.250  -0.6473   0.04209   0.03455  -0.0146   0.5690   0.3806
  -8.000  -0.5882   0.04437   0.03689  -0.0159   0.5630   0.3806
  -7.750  -0.5364   0.04638   0.03891  -0.0166   0.5579   0.3806
  -7.500  -0.4888   0.04828   0.04077  -0.0170   0.5533   0.3807
  -7.250  -0.4440   0.05004   0.04254  -0.0174   0.5488   0.3807
  -7.000  -0.6884   0.03372   0.02566  -0.0010   0.5538   0.3986
  -6.750  -0.6796   0.03280   0.02462   0.0006   0.5504   0.4015
  -6.500  -0.6434   0.03292   0.02486  -0.0007   0.5464   0.4030
  -6.250  -0.6104   0.03304   0.02504  -0.0015   0.5420   0.4047
  -6.000  -0.5799   0.03313   0.02515  -0.0020   0.5380   0.4066
  -5.750  -0.5550   0.03301   0.02501  -0.0019   0.5346   0.4090
  -5.500  -0.5372   0.03257   0.02448  -0.0011   0.5317   0.4120
  -5.250  -0.5333   0.03151   0.02322   0.0012   0.5292   0.4160
  -5.000  -0.5285   0.03058   0.02205   0.0033   0.5264   0.4194
  -4.750  -0.4962   0.03036   0.02197   0.0024   0.5232   0.4213
  -4.500  -0.4650   0.03041   0.02210   0.0017   0.5195   0.4232
  -4.250  -0.4356   0.03043   0.02216   0.0013   0.5159   0.4252
  -4.000  -0.4087   0.03032   0.02205   0.0011   0.5128   0.4274
  -3.750  -0.3840   0.03009   0.02176   0.0012   0.5101   0.4300
  -3.500  -0.3615   0.02978   0.02136   0.0015   0.5075   0.4331
  -3.250  -0.3429   0.02943   0.02083   0.0022   0.5049   0.4366
  -3.000  -0.3237   0.02906   0.02035   0.0028   0.5022   0.4394
  -2.750  -0.2949   0.02876   0.02017   0.0023   0.4991   0.4414
  -2.500  -0.2659   0.02873   0.02022   0.0018   0.4958   0.4433
  -2.250  -0.2376   0.02875   0.02028   0.0014   0.4928   0.4454
  -2.000  -0.2098   0.02875   0.02029   0.0012   0.4900   0.4479
  -1.750  -0.1830   0.02866   0.02016   0.0010   0.4875   0.4507
  -1.500  -0.1569   0.02848   0.01990   0.0009   0.4851   0.4537
  -1.250  -0.1322   0.02834   0.01962   0.0009   0.4826   0.4566
  -1.000  -0.1090   0.02836   0.01954   0.0011   0.4800   0.4592
  -0.750  -0.0833   0.02805   0.01933   0.0009   0.4772   0.4616
  -0.500  -0.0554   0.02810   0.01949   0.0005   0.4742   0.4638
  -0.250  -0.0275   0.02822   0.01969   0.0002   0.4714   0.4661
   0.000   0.0000   0.02828   0.01977   0.0000   0.4687   0.4687
   0.250   0.0275   0.02822   0.01969  -0.0002   0.4661   0.4714
   0.500   0.0553   0.02810   0.01949  -0.0005   0.4638   0.4742
   0.750   0.0833   0.02805   0.01933  -0.0009   0.4616   0.4772
   1.000   0.1091   0.02836   0.01954  -0.0011   0.4592   0.4799
   1.250   0.1322   0.02834   0.01962  -0.0009   0.4566   0.4826
   1.500   0.1569   0.02848   0.01990  -0.0009   0.4537   0.4851
   1.750   0.1830   0.02865   0.02016  -0.0010   0.4507   0.4875
   2.000   0.2098   0.02874   0.02029  -0.0012   0.4479   0.4900
   2.250   0.2376   0.02875   0.02028  -0.0015   0.4454   0.4928
   2.500   0.2659   0.02873   0.02022  -0.0018   0.4433   0.4958
   2.750   0.2949   0.02876   0.02017  -0.0023   0.4414   0.4991
   3.000   0.3238   0.02906   0.02035  -0.0028   0.4394   0.5022
   3.250   0.3429   0.02943   0.02083  -0.0022   0.4365   0.5049
   3.500   0.3616   0.02978   0.02136  -0.0015   0.4331   0.5075
   3.750   0.3842   0.03008   0.02176  -0.0012   0.4300   0.5101
   4.000   0.4088   0.03032   0.02205  -0.0011   0.4274   0.5128
   4.250   0.4357   0.03043   0.02216  -0.0013   0.4252   0.5159
   4.500   0.4651   0.03041   0.02210  -0.0018   0.4232   0.5195
   4.750   0.4963   0.03037   0.02197  -0.0024   0.4213   0.5232
   5.000   0.5286   0.03058   0.02205  -0.0034   0.4194   0.5264
   5.250   0.5335   0.03151   0.02321  -0.0012   0.4160   0.5292
   5.500   0.5375   0.03256   0.02447   0.0011   0.4120   0.5317
   5.750   0.5554   0.03301   0.02501   0.0019   0.4090   0.5346
   6.000   0.5803   0.03312   0.02514   0.0020   0.4066   0.5380
   6.250   0.6109   0.03303   0.02503   0.0014   0.4047   0.5420
   6.500   0.6438   0.03292   0.02485   0.0006   0.4030   0.5464
   6.750   0.6800   0.03280   0.02462  -0.0007   0.4015   0.5504
   7.000   0.6888   0.03371   0.02565   0.0010   0.3986   0.5538
   7.250   0.4448   0.05004   0.04254   0.0172   0.3807   0.5488
   7.500   0.4897   0.04828   0.04076   0.0168   0.3807   0.5533
   7.750   0.5371   0.04639   0.03891   0.0164   0.3806   0.5579
   8.000   0.5891   0.04437   0.03688   0.0157   0.3805   0.5630
   8.250   0.6481   0.04209   0.03455   0.0145   0.3806   0.5690
   8.500   0.7230   0.03927   0.03158   0.0119   0.3809   0.5755
   8.750   0.2259   0.09121   0.08405   0.0139   0.3204   0.5559
   9.000   0.2540   0.09110   0.08399   0.0138   0.3191   0.5601
   9.250   0.2840   0.09073   0.08364   0.0137   0.3182   0.5647
   9.500   0.3158   0.09019   0.08310   0.0137   0.3175   0.5697
   9.750   0.3486   0.08958   0.08245   0.0136   0.3169   0.5748
  10.000   0.2921   0.09945   0.09240   0.0118   0.3036   0.5747
  10.250   0.2879   0.10318   0.09618   0.0110   0.2979   0.5778
  10.500   0.3374   0.10034   0.09342   0.0114   0.3000   0.5849
  10.750   0.3794   0.09843   0.09153   0.0117   0.3009   0.5919
  11.000   0.3297   0.10788   0.10106   0.0095   0.2885   0.5922
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