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E184 (8.33%) (e184-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E184 (8.33%) (e184-il)
Reynolds number: 200,000
Max Cl/Cd: 57.99 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e184-il-200000.txt
Download as CSV file: xf-e184-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E184  (8.33%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5498   0.09894   0.09617   0.0242   1.0000   0.0493
  -9.000  -0.5499   0.09433   0.09158   0.0224   1.0000   0.0508
  -8.750  -0.6564   0.09274   0.08981   0.0191   1.0000   0.0468
  -8.500  -0.6512   0.08935   0.08644   0.0186   1.0000   0.0482
  -8.250  -0.6529   0.08502   0.08215   0.0155   1.0000   0.0491
  -8.000  -0.6584   0.08034   0.07750   0.0117   1.0000   0.0501
  -7.750  -0.6601   0.07525   0.07239   0.0078   1.0000   0.0512
  -7.500  -0.6595   0.06976   0.06683   0.0038   1.0000   0.0531
  -7.250  -0.6641   0.06431   0.06078  -0.0019   1.0000   0.0572
  -7.000  -0.6613   0.05657   0.05297  -0.0033   1.0000   0.0586
  -6.750  -0.6442   0.05321   0.04971  -0.0034   1.0000   0.0605
  -6.500  -0.6273   0.05042   0.04686  -0.0038   1.0000   0.0647
  -5.500  -0.5503   0.02779   0.02203  -0.0040   1.0000   0.0405
  -5.250  -0.5175   0.02287   0.01617  -0.0043   0.9646   0.0351
  -5.000  -0.4879   0.02087   0.01376  -0.0042   0.9412   0.0346
  -4.750  -0.4660   0.01938   0.01208  -0.0028   0.9213   0.0359
  -4.500  -0.4448   0.01845   0.01098  -0.0012   0.9052   0.0380
  -4.250  -0.4226   0.01729   0.00965   0.0005   0.8915   0.0386
  -4.000  -0.3998   0.01625   0.00849   0.0019   0.8792   0.0396
  -3.750  -0.3769   0.01539   0.00753   0.0033   0.8681   0.0415
  -3.500  -0.3540   0.01471   0.00672   0.0047   0.8581   0.0442
  -3.250  -0.3317   0.01381   0.00577   0.0060   0.8482   0.0509
  -3.000  -0.3093   0.01269   0.00493   0.0071   0.8387   0.1082
  -2.750  -0.2899   0.01150   0.00453   0.0083   0.8304   0.2866
  -2.500  -0.2704   0.01061   0.00430   0.0098   0.8215   0.4526
  -2.250  -0.2543   0.00965   0.00419   0.0124   0.8134   0.6560
  -2.000  -0.1795   0.00926   0.00450   0.0051   0.8081   0.9340
  -1.750  -0.1236   0.00957   0.00459   0.0001   0.8016   0.9738
  -1.500  -0.0619   0.00963   0.00441  -0.0068   0.7945   0.9962
  -1.250  -0.0299   0.00958   0.00420  -0.0079   0.7868   1.0000
  -1.000  -0.0065   0.00956   0.00405  -0.0072   0.7789   1.0000
  -0.750   0.0179   0.00957   0.00394  -0.0067   0.7711   1.0000
  -0.500   0.0418   0.00958   0.00384  -0.0060   0.7640   1.0000
  -0.250   0.0671   0.00961   0.00380  -0.0057   0.7562   1.0000
   0.000   0.0913   0.00965   0.00374  -0.0049   0.7495   1.0000
   0.250   0.1171   0.00970   0.00375  -0.0047   0.7417   1.0000
   0.500   0.1415   0.00976   0.00372  -0.0039   0.7353   1.0000
   0.750   0.1676   0.00983   0.00377  -0.0037   0.7273   1.0000
   1.000   0.1921   0.00990   0.00377  -0.0030   0.7210   1.0000
   1.250   0.2182   0.00997   0.00384  -0.0027   0.7123   1.0000
   1.500   0.2429   0.01004   0.00387  -0.0019   0.7049   1.0000
   1.750   0.2685   0.01010   0.00392  -0.0015   0.6957   1.0000
   2.000   0.2939   0.01016   0.00398  -0.0009   0.6867   1.0000
   2.250   0.3184   0.01021   0.00398   0.0000   0.6783   1.0000
   2.500   0.3443   0.01025   0.00406   0.0005   0.6675   1.0000
   2.750   0.3698   0.01029   0.00413   0.0011   0.6571   1.0000
   3.000   0.3950   0.01031   0.00416   0.0018   0.6464   1.0000
   3.250   0.4200   0.01033   0.00416   0.0026   0.6356   1.0000
   3.500   0.4456   0.01033   0.00423   0.0033   0.6229   1.0000
   3.750   0.4711   0.01032   0.00426   0.0040   0.6090   1.0000
   4.000   0.4965   0.01030   0.00428   0.0047   0.5938   1.0000
   4.250   0.5225   0.01028   0.00435   0.0053   0.5748   1.0000
   4.500   0.5480   0.01026   0.00440   0.0060   0.5536   1.0000
   4.750   0.5737   0.01027   0.00448   0.0066   0.5268   1.0000
   5.000   0.5990   0.01033   0.00450   0.0073   0.4782   1.0000
   5.250   0.6224   0.01096   0.00458   0.0078   0.3480   1.0000
   5.500   0.6445   0.01242   0.00529   0.0076   0.2045   1.0000
   5.750   0.6643   0.01456   0.00656   0.0074   0.0592   1.0000
   6.000   0.6856   0.01626   0.00815   0.0081   0.0320   1.0000
   6.250   0.7077   0.01736   0.00934   0.0088   0.0276   1.0000
   6.500   0.7271   0.01890   0.01092   0.0098   0.0252   1.0000
   6.750   0.7447   0.02106   0.01312   0.0112   0.0241   1.0000
   7.000   0.7659   0.02267   0.01484   0.0125   0.0238   1.0000
   7.250   0.7872   0.02467   0.01703   0.0137   0.0236   1.0000
   7.500   0.8085   0.02668   0.01927   0.0149   0.0233   1.0000
   7.750   0.8294   0.02824   0.02110   0.0159   0.0220   1.0000
   8.000   0.8481   0.03064   0.02383   0.0171   0.0215   1.0000
   8.250   0.8634   0.03399   0.02760   0.0185   0.0219   1.0000
   8.500   0.8741   0.03799   0.03200   0.0198   0.0228   1.0000
   8.750   0.8847   0.04283   0.03705   0.0208   0.0246   1.0000
  16.250   0.6077   0.18140   0.17801  -0.0282   0.0340   1.0000
  16.500   0.6093   0.18445   0.18106  -0.0302   0.0339   1.0000
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