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EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 200,000
Max Cl/Cd: 69.49 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87391-il-200000.txt
Download as CSV file: xf-ste87391-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5260   0.10468   0.10174  -0.0285   1.0019   0.0767
  -8.500  -0.6001   0.09398   0.09120  -0.0359   1.0019   0.0797
  -8.000  -0.7163   0.04588   0.04061  -0.0618   0.9964   0.0364
  -7.750  -0.6920   0.04189   0.03622  -0.0637   0.9939   0.0351
  -7.500  -0.6616   0.03793   0.03152  -0.0663   0.9921   0.0339
  -7.250  -0.6301   0.03624   0.02951  -0.0683   0.9907   0.0346
  -7.000  -0.6039   0.03471   0.02763  -0.0690   0.9882   0.0358
  -6.750  -0.5705   0.03335   0.02589  -0.0707   0.9854   0.0365
  -6.500  -0.5352   0.03242   0.02468  -0.0725   0.9838   0.0368
  -6.250  -0.5105   0.03123   0.02349  -0.0726   0.9812   0.0375
  -6.000  -0.4782   0.03051   0.02278  -0.0740   0.9781   0.0386
  -5.750  -0.4406   0.03019   0.02241  -0.0763   0.9762   0.0401
  -5.500  -0.4135   0.02948   0.02171  -0.0769   0.9712   0.0422
  -5.250  -0.3737   0.02933   0.02153  -0.0798   0.9684   0.0451
  -5.000  -0.3424   0.02876   0.02102  -0.0813   0.9630   0.0475
  -4.750  -0.2943   0.02843   0.02066  -0.0857   0.9537   0.0526
  -4.500  -0.2294   0.02765   0.01998  -0.0930   0.9404   0.0754
  -4.250  -0.1851   0.02704   0.02001  -0.0971   0.9327   0.2178
  -4.000  -0.1453   0.02724   0.02019  -0.0998   0.9283   0.2421
  -3.750  -0.1139   0.02728   0.02024  -0.1009   0.9213   0.2641
  -3.500  -0.0773   0.02739   0.02038  -0.1030   0.9168   0.2877
  -3.250  -0.0333   0.02760   0.02061  -0.1064   0.9144   0.3107
  -3.000  -0.0116   0.02742   0.02044  -0.1057   0.9061   0.3276
  -2.750   0.0288   0.02741   0.02048  -0.1084   0.9029   0.3497
  -2.500   0.0733   0.02740   0.02059  -0.1120   0.9011   0.3769
  -2.250   0.0944   0.02712   0.02045  -0.1113   0.8924   0.4078
  -2.000   0.1372   0.02683   0.02053  -0.1147   0.8898   0.4836
  -1.750   0.1761   0.02659   0.02107  -0.1164   0.8878   0.6430
  -1.500   0.1876   0.02681   0.02145  -0.1127   0.8784   0.7188
  -1.250   0.2214   0.02706   0.02164  -0.1132   0.8748   0.7569
  -1.000   0.2444   0.02727   0.02182  -0.1117   0.8685   0.7784
  -0.750   0.2680   0.02734   0.02186  -0.1103   0.8621   0.7959
  -0.500   0.3014   0.02729   0.02178  -0.1105   0.8593   0.8120
  -0.250   0.3178   0.02734   0.02181  -0.1081   0.8502   0.8256
   0.000   0.3469   0.02709   0.02155  -0.1075   0.8461   0.8379
   0.250   0.3805   0.02671   0.02113  -0.1075   0.8438   0.8496
   0.500   0.3951   0.02660   0.02102  -0.1049   0.8334   0.8608
   0.750   0.4272   0.02601   0.02041  -0.1047   0.8302   0.8715
   1.000   0.4614   0.02531   0.01970  -0.1049   0.8276   0.8810
   1.250   0.4783   0.02505   0.01944  -0.1027   0.8168   0.8907
   1.500   0.5100   0.02416   0.01855  -0.1023   0.8142   0.8997
   1.750   0.5270   0.02393   0.01832  -0.1002   0.8037   0.9085
   2.000   0.5564   0.02307   0.01747  -0.0996   0.8003   0.9175
   2.250   0.5873   0.02207   0.01649  -0.0991   0.7981   0.9281
   2.500   0.5906   0.02167   0.01612  -0.0939   0.7861   0.9445
   2.750   0.6108   0.02039   0.01487  -0.0909   0.7832   0.9700
   3.000   0.6335   0.01989   0.01442  -0.0900   0.7717   0.9981
   3.250   0.6740   0.01905   0.01359  -0.0920   0.7685   0.9981
   3.500   0.7165   0.01810   0.01266  -0.0943   0.7660   0.9981
   3.750   0.7418   0.01795   0.01254  -0.0941   0.7532   0.9981
   4.000   0.7774   0.01736   0.01197  -0.0954   0.7442   0.9981
   4.250   0.8167   0.01663   0.01125  -0.0972   0.7345   0.9981
   4.500   0.8534   0.01611   0.01075  -0.0987   0.7200   0.9981
   4.750   0.8948   0.01544   0.01006  -0.1009   0.7032   0.9981
   5.000   0.9378   0.01484   0.00939  -0.1034   0.6816   0.9981
   5.250   0.9769   0.01453   0.00898  -0.1053   0.6529   0.9981
   5.500   1.0104   0.01454   0.00879  -0.1064   0.6180   0.9981
   5.750   1.0349   0.01491   0.00897  -0.1061   0.5801   0.9981
   6.000   1.0545   0.01547   0.00935  -0.1050   0.5427   0.9981
   6.250   1.0717   0.01614   0.00984  -0.1037   0.5064   0.9981
   6.500   1.0879   0.01690   0.01041  -0.1022   0.4729   0.9981
   6.750   1.1039   0.01768   0.01104  -0.1007   0.4424   0.9981
   7.000   1.1209   0.01849   0.01168  -0.0995   0.4167   0.9981
   7.250   1.1393   0.01925   0.01233  -0.0986   0.3942   0.9981
   7.500   1.1584   0.02000   0.01298  -0.0978   0.3748   0.9981
   7.750   1.1784   0.02072   0.01365  -0.0971   0.3580   0.9981
   8.000   1.1997   0.02139   0.01432  -0.0967   0.3435   0.9981
   8.250   1.2215   0.02209   0.01498  -0.0963   0.3310   0.9981
   8.500   1.2432   0.02278   0.01563  -0.0959   0.3197   0.9981
   8.750   1.2652   0.02343   0.01634  -0.0956   0.3093   0.9981
   9.000   1.2875   0.02414   0.01697  -0.0953   0.2992   0.9981
   9.250   1.3066   0.02480   0.01776  -0.0946   0.2895   0.9981
   9.500   1.3264   0.02557   0.01844  -0.0939   0.2792   0.9981
   9.750   1.3396   0.02631   0.01932  -0.0924   0.2684   0.9981
  10.000   1.3531   0.02714   0.02017  -0.0909   0.2567   0.9981
  10.250   1.3646   0.02807   0.02103  -0.0892   0.2446   0.9981
  10.500   1.3754   0.02893   0.02203  -0.0875   0.2323   0.9981
  10.750   1.3868   0.02988   0.02305  -0.0859   0.2201   0.9981
  11.000   1.3982   0.03089   0.02407  -0.0843   0.2088   0.9981
  11.250   1.4095   0.03193   0.02516  -0.0828   0.1982   0.9981
  11.500   1.4216   0.03297   0.02629  -0.0814   0.1856   0.9981
  11.750   1.4312   0.03418   0.02755  -0.0798   0.1709   0.9981
  12.000   1.4392   0.03557   0.02895  -0.0781   0.1480   0.9981
  12.250   1.4342   0.03803   0.03110  -0.0753   0.0994   0.9981
  12.500   1.4129   0.04204   0.03464  -0.0711   0.0527   0.9981
  12.750   1.3982   0.04571   0.03817  -0.0678   0.0358   0.9981
  13.000   1.3917   0.04879   0.04129  -0.0655   0.0298   0.9981
  13.250   1.3869   0.05182   0.04441  -0.0637   0.0268   0.9981
  13.500   1.3816   0.05501   0.04770  -0.0621   0.0249   0.9981
  13.750   1.3761   0.05837   0.05120  -0.0609   0.0235   0.9981
  14.000   1.3700   0.06193   0.05487  -0.0599   0.0224   0.9981
  14.250   1.3610   0.06594   0.05898  -0.0592   0.0217   0.9981
  14.500   1.3543   0.06982   0.06301  -0.0587   0.0210   0.9981
  14.750   1.3480   0.07378   0.06710  -0.0585   0.0204   0.9981
  15.000   1.3409   0.07793   0.07136  -0.0585   0.0198   0.9981
  15.250   1.3337   0.08214   0.07566  -0.0587   0.0194   0.9981
  15.500   1.3265   0.08636   0.07993  -0.0590   0.0190   0.9981
  15.750   1.3209   0.09034   0.08398  -0.0593   0.0186   0.9981
  16.000   1.3184   0.09399   0.08775  -0.0596   0.0182   0.9981
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