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GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 599 AIRFOIL (goe599-il)
Reynolds number: 200,000
Max Cl/Cd: 61.49 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe599-il-200000.txt
Download as CSV file: xf-goe599-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 599 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4198   0.10344   0.09990  -0.0288   1.0000   0.0653
 -10.500  -0.4391   0.09749   0.09399  -0.0334   1.0000   0.0683
 -10.250  -0.5564   0.09948   0.09583  -0.0275   1.0000   0.0591
 -10.000  -0.5440   0.09807   0.09441  -0.0257   1.0000   0.0617
  -9.750  -0.4445   0.08440   0.08097  -0.0347   1.0000   0.0726
  -9.500  -0.4443   0.08082   0.07740  -0.0348   1.0000   0.0747
  -9.250  -0.4527   0.07599   0.07261  -0.0364   1.0000   0.0771
  -7.750  -0.6757   0.04143   0.03640  -0.0415   1.0000   0.0479
  -7.500  -0.6696   0.03551   0.03000  -0.0390   1.0000   0.0401
  -7.250  -0.6626   0.02993   0.02336  -0.0358   1.0000   0.0366
  -7.000  -0.6463   0.02727   0.02035  -0.0342   1.0000   0.0369
  -6.750  -0.6279   0.02512   0.01798  -0.0328   1.0000   0.0379
  -6.500  -0.6083   0.02386   0.01661  -0.0317   1.0000   0.0401
  -6.250  -0.5876   0.02252   0.01506  -0.0305   1.0000   0.0423
  -6.000  -0.5659   0.02111   0.01342  -0.0293   1.0000   0.0439
  -5.750  -0.5438   0.02009   0.01219  -0.0281   1.0000   0.0455
  -5.500  -0.5222   0.01829   0.01039  -0.0273   1.0000   0.0493
  -5.250  -0.5002   0.01749   0.00955  -0.0264   1.0000   0.0533
  -5.000  -0.4776   0.01677   0.00873  -0.0255   1.0000   0.0567
  -4.750  -0.4549   0.01585   0.00788  -0.0250   1.0000   0.0632
  -4.500  -0.4316   0.01533   0.00730  -0.0243   1.0000   0.0703
  -4.250  -0.4082   0.01493   0.00694  -0.0238   1.0000   0.0818
  -4.000  -0.3842   0.01433   0.00645  -0.0235   1.0000   0.1084
  -3.750  -0.3589   0.01322   0.00592  -0.0240   1.0000   0.2049
  -3.500  -0.3345   0.01278   0.00581  -0.0240   1.0000   0.2928
  -3.250  -0.3103   0.01252   0.00578  -0.0239   1.0000   0.3572
  -3.000  -0.2724   0.01215   0.00578  -0.0265   0.9966   0.4484
  -2.750  -0.2342   0.01193   0.00583  -0.0290   0.9933   0.5313
  -2.500  -0.1980   0.01175   0.00587  -0.0310   0.9885   0.6032
  -2.250  -0.1604   0.01158   0.00596  -0.0330   0.9847   0.6733
  -2.000  -0.1263   0.01144   0.00599  -0.0342   0.9794   0.7284
  -1.750  -0.0918   0.01132   0.00603  -0.0354   0.9741   0.7818
  -1.250  -0.0253   0.01118   0.00610  -0.0366   0.9621   0.8867
  -1.000   0.0226   0.01112   0.00605  -0.0402   0.9578   0.9382
  -0.750   0.0776   0.01102   0.00590  -0.0455   0.9521   0.9739
  -0.500   0.1360   0.01092   0.00575  -0.0519   0.9484   0.9953
  -0.250   0.1864   0.01078   0.00557  -0.0569   0.9449   1.0000
   0.000   0.2230   0.01064   0.00539  -0.0589   0.9374   1.0000
   0.250   0.2605   0.01046   0.00520  -0.0609   0.9304   1.0000
   0.500   0.2938   0.01026   0.00498  -0.0619   0.9200   1.0000
   0.750   0.3280   0.00995   0.00466  -0.0628   0.9080   1.0000
   1.000   0.3588   0.00966   0.00436  -0.0629   0.8938   1.0000
   1.250   0.3879   0.00947   0.00416  -0.0627   0.8798   1.0000
   1.500   0.4158   0.00928   0.00394  -0.0622   0.8624   1.0000
   1.750   0.4435   0.00911   0.00370  -0.0614   0.8401   1.0000
   2.000   0.4685   0.00909   0.00362  -0.0603   0.8159   1.0000
   2.250   0.4936   0.00914   0.00361  -0.0594   0.7948   1.0000
   2.500   0.5178   0.00921   0.00365  -0.0583   0.7721   1.0000
   2.750   0.5417   0.00930   0.00370  -0.0572   0.7462   1.0000
   3.000   0.5648   0.00939   0.00373  -0.0558   0.7109   1.0000
   3.250   0.5872   0.00955   0.00373  -0.0542   0.6632   1.0000
   3.500   0.6071   0.00990   0.00375  -0.0522   0.5875   1.0000
   3.750   0.6242   0.01054   0.00391  -0.0499   0.4894   1.0000
   4.000   0.6384   0.01156   0.00429  -0.0473   0.3627   1.0000
   4.250   0.6460   0.01360   0.00509  -0.0444   0.1382   1.0000
   4.500   0.6674   0.01435   0.00568  -0.0432   0.1097   1.0000
   4.750   0.6899   0.01493   0.00622  -0.0423   0.1002   1.0000
   5.000   0.7123   0.01551   0.00683  -0.0413   0.0942   1.0000
   5.250   0.7345   0.01612   0.00745  -0.0403   0.0894   1.0000
   5.500   0.7544   0.01704   0.00833  -0.0390   0.0857   1.0000
   5.750   0.7769   0.01776   0.00911  -0.0380   0.0832   1.0000
   6.000   0.7997   0.01847   0.00988  -0.0371   0.0793   1.0000
   6.250   0.8219   0.01937   0.01075  -0.0362   0.0750   1.0000
   6.500   0.8444   0.02065   0.01206  -0.0354   0.0707   1.0000
   6.750   0.8681   0.02145   0.01296  -0.0347   0.0660   1.0000
   7.000   0.8915   0.02295   0.01440  -0.0342   0.0607   1.0000
   7.250   0.9149   0.02431   0.01598  -0.0334   0.0556   1.0000
   7.500   0.9381   0.02557   0.01734  -0.0327   0.0507   1.0000
   7.750   0.9607   0.02832   0.02019  -0.0322   0.0460   1.0000
   8.000   0.9818   0.02923   0.02139  -0.0309   0.0423   1.0000
   8.250   1.0033   0.03079   0.02310  -0.0299   0.0395   1.0000
   8.500   1.0232   0.03287   0.02525  -0.0292   0.0372   1.0000
   8.750   1.0373   0.03575   0.02856  -0.0272   0.0352   1.0000
   9.000   1.0513   0.03784   0.03108  -0.0250   0.0332   1.0000
   9.250   1.0617   0.04094   0.03460  -0.0226   0.0323   1.0000
   9.500   1.0674   0.04446   0.03853  -0.0199   0.0317   1.0000
   9.750   1.0666   0.04866   0.04317  -0.0167   0.0317   1.0000
  10.000   1.0588   0.05335   0.04829  -0.0131   0.0322   1.0000
  10.250   1.0465   0.05788   0.05318  -0.0097   0.0326   1.0000
  10.500   1.0289   0.06201   0.05757  -0.0061   0.0331   1.0000
  10.750   1.0074   0.06594   0.06171  -0.0029   0.0335   1.0000
  11.000   0.9855   0.07022   0.06618  -0.0012   0.0339   1.0000
  11.250   0.9641   0.07502   0.07112  -0.0010   0.0344   1.0000
  11.500   0.9429   0.08048   0.07670  -0.0023   0.0350   1.0000
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