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GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 564 AIRFOIL (goe564-il)
Reynolds number: 200,000
Max Cl/Cd: 65.62 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe564-il-200000-n5.txt
Download as CSV file: xf-goe564-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 564 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4710   0.08608   0.08245  -0.0336   1.0000   0.0200
  -9.000  -0.4815   0.08156   0.07800  -0.0347   1.0000   0.0202
  -8.750  -0.4955   0.07738   0.07390  -0.0354   1.0000   0.0202
  -8.500  -0.5164   0.07356   0.07019  -0.0353   1.0000   0.0203
  -8.250  -0.5340   0.06825   0.06494  -0.0374   1.0000   0.0202
  -8.000  -0.5526   0.06148   0.05816  -0.0401   1.0000   0.0203
  -7.750  -0.5784   0.05080   0.04729  -0.0433   1.0000   0.0204
  -7.500  -0.5925   0.02898   0.02361  -0.0517   0.9936   0.0224
  -7.250  -0.5681   0.02689   0.02125  -0.0526   0.9903   0.0240
  -7.000  -0.5398   0.02593   0.02016  -0.0537   0.9877   0.0255
  -6.750  -0.5115   0.02415   0.01801  -0.0547   0.9851   0.0274
  -6.500  -0.4843   0.02277   0.01622  -0.0551   0.9811   0.0298
  -6.250  -0.4548   0.02114   0.01423  -0.0560   0.9779   0.0318
  -6.000  -0.4232   0.02002   0.01297  -0.0574   0.9755   0.0339
  -5.750  -0.3965   0.01939   0.01223  -0.0574   0.9708   0.0363
  -5.500  -0.3659   0.01849   0.01111  -0.0582   0.9674   0.0384
  -5.250  -0.3332   0.01774   0.01013  -0.0593   0.9649   0.0404
  -5.000  -0.3057   0.01684   0.00911  -0.0594   0.9607   0.0422
  -4.750  -0.2768   0.01610   0.00831  -0.0598   0.9563   0.0440
  -4.500  -0.2442   0.01551   0.00764  -0.0608   0.9532   0.0458
  -4.250  -0.2103   0.01500   0.00705  -0.0621   0.9509   0.0484
  -4.000  -0.1859   0.01461   0.00658  -0.0614   0.9451   0.0510
  -3.750  -0.1561   0.01413   0.00607  -0.0618   0.9415   0.0538
  -3.500  -0.1238   0.01371   0.00565  -0.0628   0.9388   0.0586
  -3.250  -0.0897   0.01333   0.00527  -0.0641   0.9367   0.0662
  -3.000  -0.0652   0.01309   0.00505  -0.0633   0.9305   0.0782
  -2.750  -0.0342   0.01287   0.00484  -0.0640   0.9267   0.0930
  -2.500  -0.0003   0.01266   0.00462  -0.0652   0.9239   0.1062
  -2.250   0.0348   0.01245   0.00442  -0.0667   0.9216   0.1196
  -2.000   0.0588   0.01229   0.00430  -0.0659   0.9143   0.1311
  -1.750   0.0907   0.01206   0.00412  -0.0667   0.9102   0.1443
  -1.500   0.1251   0.01181   0.00391  -0.0680   0.9071   0.1584
  -1.250   0.1504   0.01162   0.00379  -0.0674   0.8996   0.1766
  -1.000   0.1822   0.01130   0.00361  -0.0682   0.8947   0.2080
  -0.750   0.2106   0.01091   0.00347  -0.0683   0.8879   0.2751
  -0.500   0.2386   0.01012   0.00331  -0.0684   0.8793   0.4617
  -0.250   0.2597   0.00922   0.00324  -0.0665   0.8668   0.7003
   0.000   0.3345   0.00868   0.00319  -0.0754   0.8553   0.9495
   0.250   0.3921   0.00859   0.00303  -0.0815   0.8429   0.9904
   0.500   0.4292   0.00856   0.00291  -0.0832   0.8265   1.0000
   0.750   0.4567   0.00855   0.00278  -0.0828   0.8056   1.0000
   1.000   0.4809   0.00859   0.00270  -0.0817   0.7784   1.0000
   1.250   0.5048   0.00865   0.00265  -0.0806   0.7501   1.0000
   1.500   0.5285   0.00873   0.00261  -0.0794   0.7178   1.0000
   1.750   0.5516   0.00887   0.00258  -0.0782   0.6824   1.0000
   2.000   0.5740   0.00906   0.00259  -0.0768   0.6523   1.0000
   2.250   0.5959   0.00928   0.00266  -0.0754   0.6253   1.0000
   2.500   0.6175   0.00953   0.00276  -0.0739   0.5985   1.0000
   2.750   0.6387   0.00978   0.00291  -0.0724   0.5682   1.0000
   3.000   0.6595   0.01005   0.00305  -0.0709   0.5308   1.0000
   3.250   0.6784   0.01041   0.00320  -0.0689   0.4804   1.0000
   3.500   0.6954   0.01089   0.00340  -0.0667   0.4216   1.0000
   3.750   0.7124   0.01144   0.00366  -0.0646   0.3633   1.0000
   4.000   0.7310   0.01194   0.00394  -0.0629   0.3177   1.0000
   4.250   0.7510   0.01240   0.00424  -0.0614   0.2842   1.0000
   4.500   0.7717   0.01281   0.00456  -0.0601   0.2605   1.0000
   4.750   0.7931   0.01320   0.00489  -0.0589   0.2439   1.0000
   5.000   0.8146   0.01358   0.00522  -0.0577   0.2279   1.0000
   5.250   0.8362   0.01396   0.00557  -0.0566   0.2144   1.0000
   5.500   0.8581   0.01433   0.00594  -0.0555   0.2012   1.0000
   5.750   0.8805   0.01467   0.00630  -0.0545   0.1903   1.0000
   6.000   0.9026   0.01503   0.00668  -0.0535   0.1787   1.0000
   6.250   0.9244   0.01540   0.00707  -0.0524   0.1669   1.0000
   6.500   0.9462   0.01579   0.00748  -0.0513   0.1519   1.0000
   6.750   0.9676   0.01621   0.00787  -0.0503   0.1304   1.0000
   7.250   1.0064   0.01744   0.00886  -0.0476   0.0876   1.0000
   7.500   1.0255   0.01810   0.00952  -0.0462   0.0742   1.0000
   7.750   1.0448   0.01876   0.01018  -0.0449   0.0513   1.0000
   8.000   1.0616   0.01967   0.01096  -0.0432   0.0379   1.0000
   8.250   1.0782   0.02059   0.01190  -0.0414   0.0320   1.0000
   8.500   1.0948   0.02146   0.01286  -0.0396   0.0278   1.0000
   8.750   1.1079   0.02259   0.01407  -0.0374   0.0247   1.0000
   9.000   1.1238   0.02342   0.01504  -0.0355   0.0230   1.0000
   9.250   1.1382   0.02434   0.01611  -0.0335   0.0210   1.0000
   9.500   1.1509   0.02527   0.01714  -0.0312   0.0194   1.0000
   9.750   1.1583   0.02655   0.01849  -0.0283   0.0178   1.0000
  10.000   1.1668   0.02777   0.01982  -0.0256   0.0171   1.0000
  10.250   1.1765   0.02895   0.02115  -0.0231   0.0163   1.0000
  10.500   1.1851   0.03025   0.02259  -0.0206   0.0156   1.0000
  10.750   1.1931   0.03160   0.02407  -0.0182   0.0149   1.0000
  11.000   1.2007   0.03296   0.02556  -0.0160   0.0142   1.0000
  11.250   1.2076   0.03433   0.02704  -0.0139   0.0136   1.0000
  11.500   1.2122   0.03585   0.02864  -0.0118   0.0129   1.0000
  11.750   1.2141   0.03784   0.03079  -0.0096   0.0125   1.0000
  12.000   1.2141   0.04020   0.03330  -0.0075   0.0121   1.0000
  12.250   1.2159   0.04238   0.03569  -0.0057   0.0119   1.0000
  12.500   1.2158   0.04481   0.03832  -0.0042   0.0117   1.0000
  12.750   1.2135   0.04752   0.04126  -0.0028   0.0114   1.0000
  13.000   1.2097   0.05051   0.04445  -0.0018   0.0113   1.0000
  13.250   1.2034   0.05385   0.04802  -0.0013   0.0111   1.0000
  13.500   1.1948   0.05768   0.05207  -0.0012   0.0109   1.0000
  13.750   1.1851   0.06188   0.05647  -0.0018   0.0109   1.0000
  14.000   1.1731   0.06667   0.06149  -0.0031   0.0108   1.0000
  14.250   1.1590   0.07212   0.06715  -0.0052   0.0107   1.0000
  14.500   1.1442   0.07808   0.07332  -0.0080   0.0107   1.0000
  14.750   1.1268   0.08502   0.08046  -0.0117   0.0107   1.0000
  15.000   1.1084   0.09275   0.08839  -0.0164   0.0106   1.0000
  15.250   1.0863   0.10194   0.09777  -0.0220   0.0107   1.0000
  15.500   1.0647   0.11163   0.10764  -0.0280   0.0109   1.0000
  15.750   1.0401   0.12261   0.11878  -0.0348   0.0111   1.0000
  16.000   1.0133   0.13478   0.13108  -0.0421   0.0113   1.0000
  16.250   0.9810   0.14927   0.14567  -0.0504   0.0116   1.0000
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