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GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 599 AIRFOIL (goe599-il)
Reynolds number: 50,000
Max Cl/Cd: 33.1 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe599-il-50000-n5.txt
Download as CSV file: xf-goe599-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5596   0.09562   0.08842  -0.0307   1.0000   0.0496
  -9.750  -0.5674   0.08954   0.08242  -0.0342   1.0000   0.0493
  -9.500  -0.5792   0.08225   0.07520  -0.0390   1.0000   0.0486
  -9.250  -0.5992   0.07505   0.06804  -0.0442   1.0000   0.0473
  -9.000  -0.6226   0.06917   0.06211  -0.0464   1.0000   0.0462
  -8.750  -0.6389   0.06404   0.05682  -0.0472   1.0000   0.0459
  -8.500  -0.6475   0.05975   0.05233  -0.0469   1.0000   0.0464
  -8.250  -0.6513   0.05579   0.04811  -0.0461   1.0000   0.0474
  -8.000  -0.6517   0.05189   0.04388  -0.0451   1.0000   0.0486
  -7.750  -0.6484   0.04802   0.03958  -0.0438   1.0000   0.0498
  -7.500  -0.6410   0.04423   0.03529  -0.0424   1.0000   0.0510
  -7.250  -0.6295   0.04073   0.03123  -0.0410   1.0000   0.0524
  -7.000  -0.6151   0.03779   0.02777  -0.0396   1.0000   0.0554
  -6.750  -0.5983   0.03595   0.02584  -0.0385   1.0000   0.0594
  -6.500  -0.5795   0.03373   0.02327  -0.0372   1.0000   0.0631
  -6.250  -0.5593   0.03169   0.02086  -0.0359   1.0000   0.0681
  -6.000  -0.5399   0.03039   0.01951  -0.0348   1.0000   0.0750
  -5.750  -0.5185   0.02880   0.01768  -0.0334   1.0000   0.0812
  -5.500  -0.4977   0.02769   0.01636  -0.0323   1.0000   0.0921
  -5.250  -0.4773   0.02637   0.01498  -0.0311   1.0000   0.1031
  -5.000  -0.4565   0.02501   0.01357  -0.0299   1.0000   0.1162
  -4.750  -0.4359   0.02368   0.01236  -0.0290   1.0000   0.1412
  -4.500  -0.4142   0.02249   0.01143  -0.0285   1.0000   0.1844
  -4.250  -0.3930   0.02156   0.01072  -0.0278   1.0000   0.2457
  -4.000  -0.3731   0.02074   0.01027  -0.0269   1.0000   0.3347
  -3.750  -0.3541   0.02008   0.01006  -0.0255   1.0000   0.4293
  -3.500  -0.3340   0.01967   0.00984  -0.0239   1.0000   0.4958
  -3.250  -0.3131   0.01938   0.00959  -0.0225   1.0000   0.5507
  -3.000  -0.2927   0.01913   0.00937  -0.0208   1.0000   0.6067
  -2.750  -0.2735   0.01890   0.00927  -0.0187   1.0000   0.6672
  -2.500  -0.2550   0.01871   0.00923  -0.0162   1.0000   0.7292
  -2.250  -0.2358   0.01859   0.00923  -0.0136   1.0000   0.7963
  -2.000  -0.2081   0.01857   0.00920  -0.0127   1.0000   0.8736
  -1.750  -0.1598   0.01862   0.00910  -0.0168   1.0000   0.9608
  -1.500  -0.1302   0.01860   0.00883  -0.0185   1.0000   1.0000
  -1.250  -0.1141   0.01866   0.00868  -0.0175   1.0000   1.0000
  -1.000  -0.0961   0.01880   0.00862  -0.0167   1.0000   1.0000
  -0.750  -0.0770   0.01899   0.00864  -0.0161   1.0000   1.0000
  -0.500  -0.0454   0.01927   0.00874  -0.0179   0.9955   1.0000
  -0.250  -0.0057   0.01960   0.00891  -0.0211   0.9873   1.0000
   0.000   0.0336   0.01991   0.00910  -0.0242   0.9784   1.0000
   0.250   0.0725   0.02021   0.00930  -0.0272   0.9686   1.0000
   0.500   0.1116   0.02048   0.00951  -0.0301   0.9581   1.0000
   0.750   0.1518   0.02072   0.00971  -0.0330   0.9470   1.0000
   1.000   0.1935   0.02092   0.00990  -0.0362   0.9358   1.0000
   1.250   0.2303   0.02106   0.01006  -0.0383   0.9225   1.0000
   1.500   0.2667   0.02118   0.01022  -0.0402   0.9091   1.0000
   1.750   0.3030   0.02128   0.01038  -0.0420   0.8959   1.0000
   2.000   0.3397   0.02136   0.01055  -0.0438   0.8829   1.0000
   2.250   0.3762   0.02141   0.01071  -0.0454   0.8700   1.0000
   2.500   0.4113   0.02145   0.01089  -0.0466   0.8568   1.0000
   2.750   0.4457   0.02148   0.01105  -0.0477   0.8433   1.0000
   3.000   0.4796   0.02149   0.01123  -0.0485   0.8289   1.0000
   3.250   0.5165   0.02124   0.01116  -0.0492   0.8099   1.0000
   3.500   0.5487   0.02098   0.01105  -0.0488   0.7845   1.0000
   3.750   0.5788   0.02070   0.01092  -0.0478   0.7545   1.0000
   4.000   0.6061   0.02039   0.01070  -0.0461   0.7161   1.0000
   4.250   0.6293   0.02017   0.01048  -0.0437   0.6634   1.0000
   4.500   0.6521   0.02009   0.01024  -0.0412   0.5948   1.0000
   4.750   0.6739   0.02036   0.01031  -0.0390   0.5211   1.0000
   5.000   0.6912   0.02106   0.01056  -0.0363   0.4255   1.0000
   5.250   0.7025   0.02242   0.01120  -0.0334   0.2845   1.0000
   5.500   0.7117   0.02453   0.01230  -0.0312   0.1691   1.0000
   5.750   0.7285   0.02603   0.01363  -0.0297   0.1430   1.0000
   6.000   0.7471   0.02727   0.01490  -0.0284   0.1310   1.0000
   6.250   0.7668   0.02844   0.01615  -0.0272   0.1228   1.0000
   6.500   0.7882   0.02962   0.01745  -0.0261   0.1170   1.0000
   6.750   0.8113   0.03079   0.01877  -0.0252   0.1103   1.0000
   7.000   0.8347   0.03207   0.02017  -0.0246   0.1031   1.0000
   7.250   0.8614   0.03346   0.02175  -0.0241   0.0976   1.0000
   7.500   0.8899   0.03529   0.02355  -0.0241   0.0929   1.0000
   7.750   0.9138   0.03691   0.02554  -0.0234   0.0851   1.0000
   8.000   0.9374   0.03900   0.02768  -0.0230   0.0784   1.0000
   8.250   0.9568   0.04102   0.03007  -0.0219   0.0708   1.0000
   8.500   0.9770   0.04384   0.03303  -0.0212   0.0655   1.0000
   8.750   0.9901   0.04655   0.03640  -0.0192   0.0599   1.0000
   9.000   1.0040   0.04949   0.03964  -0.0178   0.0561   1.0000
   9.250   1.0165   0.05328   0.04345  -0.0169   0.0530   1.0000
   9.500   1.0154   0.05643   0.04734  -0.0137   0.0507   1.0000
   9.750   1.0118   0.06000   0.05143  -0.0110   0.0486   1.0000
  10.000   1.0051   0.06371   0.05555  -0.0084   0.0473   1.0000
  10.250   0.9942   0.06757   0.05974  -0.0060   0.0467   1.0000
  10.500   0.9774   0.07131   0.06375  -0.0034   0.0464   1.0000
  10.750   0.9576   0.07546   0.06812  -0.0018   0.0464   1.0000
  11.000   0.9352   0.08027   0.07313  -0.0018   0.0465   1.0000
  11.250   0.9110   0.08603   0.07905  -0.0035   0.0469   1.0000
  11.500   0.8860   0.09297   0.08611  -0.0072   0.0475   1.0000
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