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GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 777 AIRFOIL (goe777-il)
Reynolds number: 100,000
Max Cl/Cd: 32.05 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe777-il-100000-n5.txt
Download as CSV file: xf-goe777-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 777 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.2807   0.10631   0.09977  -0.0557   0.6488   0.0573
 -13.000  -0.5134   0.06105   0.05388  -0.0886   0.6661   0.0573
 -12.750  -0.5286   0.05701   0.04964  -0.0905   0.6614   0.0577
 -12.500  -0.5385   0.05381   0.04626  -0.0915   0.6559   0.0582
 -12.250  -0.5465   0.05103   0.04328  -0.0915   0.6507   0.0588
 -12.000  -0.5538   0.04848   0.04047  -0.0907   0.6460   0.0595
 -11.750  -0.5618   0.04628   0.03797  -0.0887   0.6420   0.0602
 -11.500  -0.5660   0.04402   0.03540  -0.0868   0.6376   0.0611
 -11.250  -0.5680   0.04167   0.03263  -0.0849   0.6332   0.0624
 -11.000  -0.5502   0.04086   0.03180  -0.0841   0.6286   0.0634
 -10.750  -0.5348   0.03988   0.03069  -0.0831   0.6248   0.0646
 -10.500  -0.5210   0.03863   0.02921  -0.0819   0.6215   0.0662
 -10.250  -0.5084   0.03708   0.02727  -0.0805   0.6185   0.0680
 -10.000  -0.4890   0.03603   0.02614  -0.0798   0.6149   0.0693
  -9.750  -0.4682   0.03522   0.02530  -0.0792   0.6115   0.0708
  -9.500  -0.4485   0.03430   0.02421  -0.0784   0.6083   0.0730
  -9.250  -0.4290   0.03326   0.02289  -0.0774   0.6054   0.0755
  -9.000  -0.4059   0.03259   0.02221  -0.0769   0.6026   0.0773
  -8.750  -0.3834   0.03184   0.02133  -0.0763   0.6000   0.0797
  -8.500  -0.3613   0.03104   0.02024  -0.0755   0.5974   0.0827
  -8.250  -0.3372   0.03041   0.01972  -0.0752   0.5943   0.0850
  -8.000  -0.3136   0.02982   0.01908  -0.0747   0.5914   0.0881
  -7.750  -0.2898   0.02920   0.01834  -0.0741   0.5888   0.0914
  -7.500  -0.2656   0.02866   0.01785  -0.0737   0.5864   0.0944
  -7.250  -0.2414   0.02819   0.01727  -0.0732   0.5841   0.0983
  -7.000  -0.2172   0.02767   0.01674  -0.0727   0.5819   0.1017
  -6.750  -0.1930   0.02725   0.01630  -0.0721   0.5799   0.1057
  -6.500  -0.1683   0.02687   0.01580  -0.0716   0.5779   0.1101
  -6.250  -0.1447   0.02647   0.01544  -0.0710   0.5758   0.1143
  -6.000  -0.1210   0.02620   0.01517  -0.0704   0.5732   0.1193
  -5.750  -0.0981   0.02587   0.01492  -0.0698   0.5708   0.1239
  -5.500  -0.0747   0.02563   0.01470  -0.0692   0.5685   0.1293
  -5.250  -0.0516   0.02537   0.01447  -0.0685   0.5663   0.1346
  -5.000  -0.0284   0.02512   0.01424  -0.0678   0.5639   0.1407
  -4.750  -0.0048   0.02488   0.01399  -0.0671   0.5615   0.1473
  -4.500   0.0187   0.02461   0.01374  -0.0664   0.5592   0.1558
  -4.250   0.0425   0.02433   0.01349  -0.0657   0.5571   0.1673
  -4.000   0.0664   0.02403   0.01324  -0.0650   0.5549   0.1870
  -3.750   0.0865   0.02372   0.01323  -0.0640   0.5512   0.2274
  -3.500   0.1060   0.02340   0.01325  -0.0629   0.5467   0.2923
  -3.250   0.1276   0.02312   0.01317  -0.0618   0.5425   0.3509
  -3.000   0.1502   0.02283   0.01306  -0.0609   0.5390   0.4039
  -2.500   0.1978   0.02251   0.01311  -0.0588   0.5338   0.5223
  -2.250   0.2223   0.02263   0.01326  -0.0580   0.5313   0.5698
  -2.000   0.2428   0.02289   0.01368  -0.0567   0.5276   0.6089
  -1.750   0.2644   0.02311   0.01400  -0.0555   0.5239   0.6426
  -1.500   0.2876   0.02328   0.01423  -0.0544   0.5205   0.6706
  -1.250   0.3121   0.02339   0.01435  -0.0535   0.5175   0.6955
  -1.000   0.3379   0.02346   0.01440  -0.0527   0.5148   0.7194
  -0.750   0.3650   0.02350   0.01439  -0.0521   0.5124   0.7430
  -0.500   0.3922   0.02360   0.01444  -0.0514   0.5099   0.7656
  -0.250   0.4099   0.02405   0.01506  -0.0499   0.5052   0.7857
   0.000   0.4313   0.02434   0.01540  -0.0488   0.5009   0.8047
   0.250   0.4566   0.02450   0.01556  -0.0482   0.4972   0.8213
   0.500   0.4846   0.02456   0.01557  -0.0480   0.4942   0.8366
   0.750   0.5146   0.02457   0.01548  -0.0481   0.4916   0.8529
   1.000   0.5473   0.02457   0.01537  -0.0487   0.4894   0.8702
   1.250   0.5648   0.02531   0.01631  -0.0476   0.4834   0.8916
   1.500   0.5960   0.02567   0.01670  -0.0485   0.4786   0.9129
   1.750   0.6357   0.02579   0.01675  -0.0507   0.4748   0.9308
   2.000   0.6802   0.02574   0.01657  -0.0538   0.4718   0.9441
   2.250   0.7181   0.02595   0.01672  -0.0561   0.4680   0.9571
   2.500   0.7468   0.02672   0.01759  -0.0578   0.4615   0.9733
   2.750   0.7856   0.02693   0.01775  -0.0606   0.4573   0.9859
   3.000   0.8293   0.02689   0.01761  -0.0640   0.4541   0.9965
   3.250   0.8574   0.02675   0.01732  -0.0643   0.4517   1.0000
   3.500   0.8355   0.02795   0.01867  -0.0576   0.4448   1.0000
   3.750   0.8410   0.02836   0.01905  -0.0546   0.4404   1.0000
   4.000   0.8597   0.02838   0.01898  -0.0532   0.4373   1.0000
   4.250   0.8861   0.02821   0.01868  -0.0529   0.4349   1.0000
   4.500   0.8530   0.03021   0.02084  -0.0454   0.4268   1.0000
   4.750   0.8607   0.03076   0.02135  -0.0430   0.4226   1.0000
   5.000   0.8855   0.03072   0.02121  -0.0426   0.4200   1.0000
   5.250   0.8424   0.03440   0.02504  -0.0369   0.4111   1.0000
   5.500   0.8495   0.03567   0.02629  -0.0358   0.4067   1.0000
   5.750   0.8763   0.03559   0.02612  -0.0356   0.4046   1.0000
   6.000   0.9077   0.03520   0.02565  -0.0357   0.4030   1.0000
   6.250   0.8409   0.04303   0.03366  -0.0327   0.3901   1.0000
   6.500   0.8700   0.04267   0.03323  -0.0326   0.3887   1.0000
   6.750   0.9019   0.04207   0.03256  -0.0325   0.3876   1.0000
   7.250   0.8288   0.05497   0.04562  -0.0307   0.3686   1.0000
   7.500   0.8781   0.05225   0.04281  -0.0306   0.3705   1.0000
   8.500   0.8931   0.06206   0.05266  -0.0295   0.3558   1.0000
  11.500   0.5470   0.12356   0.11559  -0.0174   0.2801   1.0000
  11.750   0.5593   0.12460   0.11664  -0.0174   0.2779   1.0000
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