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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 50,000
Max Cl/Cd: 39.06 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe602-il-50000-n5.txt
Download as CSV file: xf-goe602-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3642   0.11576   0.10871  -0.0349   1.0000   0.1047
  -9.500  -0.3773   0.11425   0.10733  -0.0369   1.0000   0.1088
  -9.000  -0.3819   0.10378   0.09696  -0.0405   1.0000   0.0666
  -8.750  -0.3789   0.10036   0.09359  -0.0395   1.0000   0.0656
  -8.500  -0.3793   0.09722   0.09052  -0.0388   1.0000   0.0641
  -8.250  -0.3838   0.09421   0.08760  -0.0383   1.0000   0.0626
  -8.000  -0.3922   0.09129   0.08481  -0.0376   1.0000   0.0611
  -7.750  -0.4045   0.08856   0.08220  -0.0368   1.0000   0.0597
  -7.250  -0.4367   0.07866   0.07249  -0.0434   1.0000   0.0537
  -7.000  -0.4395   0.07518   0.06903  -0.0430   1.0000   0.0533
  -6.750  -0.4418   0.07145   0.06528  -0.0429   1.0000   0.0529
  -6.500  -0.4426   0.06762   0.06141  -0.0431   1.0000   0.0524
  -6.250  -0.4418   0.06345   0.05708  -0.0436   1.0000   0.0521
  -6.000  -0.4383   0.05911   0.05256  -0.0443   1.0000   0.0519
  -5.750  -0.4316   0.05446   0.04758  -0.0454   1.0000   0.0525
  -5.500  -0.4208   0.04984   0.04240  -0.0466   1.0000   0.0537
  -5.250  -0.4087   0.04679   0.03924  -0.0463   1.0000   0.0559
  -5.000  -0.3932   0.04378   0.03593  -0.0462   1.0000   0.0572
  -4.750  -0.3751   0.04061   0.03231  -0.0463   1.0000   0.0585
  -4.500  -0.3555   0.03813   0.02939  -0.0461   1.0000   0.0623
  -4.250  -0.3329   0.03556   0.02610  -0.0460   1.0000   0.0662
  -4.000  -0.2985   0.03297   0.02297  -0.0479   0.9955   0.0688
  -3.750  -0.2641   0.03153   0.02126  -0.0500   0.9897   0.0754
  -3.500  -0.2274   0.03002   0.01913  -0.0516   0.9841   0.0809
  -3.250  -0.1927   0.02864   0.01763  -0.0532   0.9782   0.0849
  -3.000  -0.1585   0.02763   0.01641  -0.0544   0.9716   0.0904
  -2.750  -0.1213   0.02687   0.01546  -0.0565   0.9655   0.1013
  -2.500  -0.0886   0.02618   0.01462  -0.0576   0.9575   0.1140
  -2.250  -0.0514   0.02542   0.01376  -0.0596   0.9509   0.1319
  -2.000  -0.0175   0.02445   0.01300  -0.0612   0.9428   0.1799
  -1.750   0.0163   0.02328   0.01282  -0.0631   0.9358   0.3907
  -1.500   0.0563   0.02146   0.01289  -0.0634   0.9297   1.0000
  -1.250   0.0932   0.02163   0.01257  -0.0655   0.9206   1.0000
  -1.000   0.1305   0.02180   0.01234  -0.0676   0.9114   1.0000
  -0.750   0.1622   0.02194   0.01218  -0.0686   0.9004   1.0000
  -0.500   0.1966   0.02209   0.01203  -0.0701   0.8904   1.0000
  -0.250   0.2351   0.02219   0.01189  -0.0722   0.8818   1.0000
   0.250   0.2963   0.02244   0.01177  -0.0735   0.8591   1.0000
   0.500   0.3306   0.02250   0.01169  -0.0747   0.8492   1.0000
   0.750   0.3668   0.02251   0.01157  -0.0761   0.8398   1.0000
   1.250   0.4252   0.02272   0.01161  -0.0765   0.8158   1.0000
   1.500   0.4560   0.02277   0.01160  -0.0769   0.8044   1.0000
   1.750   0.4905   0.02272   0.01151  -0.0778   0.7943   1.0000
   2.000   0.5215   0.02273   0.01150  -0.0781   0.7828   1.0000
   2.250   0.5498   0.02280   0.01157  -0.0780   0.7698   1.0000
   2.500   0.5785   0.02287   0.01163  -0.0779   0.7570   1.0000
   2.750   0.6080   0.02291   0.01170  -0.0779   0.7442   1.0000
   3.000   0.6379   0.02294   0.01176  -0.0779   0.7313   1.0000
   3.500   0.6979   0.02301   0.01192  -0.0778   0.7046   1.0000
   3.750   0.7270   0.02307   0.01204  -0.0776   0.6904   1.0000
   4.000   0.7553   0.02318   0.01220  -0.0773   0.6756   1.0000
   4.250   0.7828   0.02333   0.01245  -0.0769   0.6602   1.0000
   4.500   0.8098   0.02351   0.01270  -0.0763   0.6446   1.0000
   4.750   0.8364   0.02372   0.01300  -0.0758   0.6288   1.0000
   5.000   0.8627   0.02397   0.01338  -0.0752   0.6129   1.0000
   5.250   0.8887   0.02424   0.01375  -0.0745   0.5969   1.0000
   5.500   0.9145   0.02454   0.01417  -0.0738   0.5809   1.0000
   5.750   0.9402   0.02487   0.01466  -0.0731   0.5647   1.0000
   6.000   0.9646   0.02522   0.01513  -0.0722   0.5475   1.0000
   6.250   0.9855   0.02567   0.01574  -0.0708   0.5284   1.0000
   6.500   1.0075   0.02602   0.01621  -0.0694   0.5081   1.0000
   6.750   1.0269   0.02640   0.01670  -0.0676   0.4856   1.0000
   7.000   1.0459   0.02678   0.01723  -0.0657   0.4625   1.0000
   7.250   1.0598   0.02723   0.01775  -0.0631   0.4349   1.0000
   7.500   1.0671   0.02768   0.01814  -0.0594   0.3977   1.0000
   7.750   1.0718   0.02830   0.01865  -0.0556   0.3570   1.0000
   8.000   1.0794   0.02910   0.01947  -0.0525   0.3220   1.0000
   8.250   1.0846   0.03003   0.02034  -0.0492   0.2853   1.0000
   8.500   1.0861   0.03129   0.02143  -0.0457   0.2387   1.0000
   8.750   1.0845   0.03304   0.02287  -0.0423   0.1805   1.0000
   9.000   1.0784   0.03549   0.02482  -0.0391   0.1189   1.0000
   9.250   1.0737   0.03816   0.02726  -0.0364   0.0851   1.0000
   9.500   1.0722   0.04068   0.02974  -0.0341   0.0662   1.0000
   9.750   1.0718   0.04316   0.03223  -0.0322   0.0550   1.0000
  10.000   1.0713   0.04571   0.03483  -0.0306   0.0494   1.0000
  10.250   1.0688   0.04854   0.03771  -0.0293   0.0460   1.0000
  10.500   1.0665   0.05147   0.04073  -0.0282   0.0441   1.0000
  10.750   1.0653   0.05442   0.04386  -0.0272   0.0425   1.0000
  11.000   1.0644   0.05743   0.04705  -0.0265   0.0409   1.0000
  11.250   1.0638   0.06052   0.05029  -0.0259   0.0393   1.0000
  11.500   1.0631   0.06369   0.05356  -0.0255   0.0377   1.0000
  11.750   1.0628   0.06689   0.05683  -0.0250   0.0362   1.0000
  12.000   1.0681   0.06963   0.05976  -0.0242   0.0348   1.0000
  12.250   1.0767   0.07214   0.06254  -0.0232   0.0337   1.0000
  12.500   1.0872   0.07468   0.06535  -0.0221   0.0329   1.0000
  12.750   1.0963   0.07760   0.06857  -0.0213   0.0322   1.0000
  13.000   1.0999   0.08121   0.07247  -0.0211   0.0316   1.0000
  13.250   1.0983   0.08542   0.07706  -0.0216   0.0311   1.0000
  13.500   1.0929   0.09014   0.08204  -0.0227   0.0308   1.0000
  13.750   1.0842   0.09542   0.08757  -0.0244   0.0305   1.0000
  14.000   1.0726   0.10133   0.09373  -0.0269   0.0304   1.0000
  14.250   1.0583   0.10803   0.10068  -0.0302   0.0305   1.0000
  14.500   1.0418   0.11562   0.10850  -0.0345   0.0307   1.0000
  14.750   1.0229   0.12441   0.11751  -0.0397   0.0312   1.0000
  15.000   1.0034   0.13418   0.12738  -0.0457   0.0319   1.0000
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