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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 50,000
Max Cl/Cd: 36 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe623-il-50000-n5.txt
Download as CSV file: xf-goe623-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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  -0.3785   0.10474   0.09763  -0.0418   1.0000   0.0696
  -9.500  -0.3742   0.10121   0.09413  -0.0420   1.0000   0.0690
  -9.250  -0.3740   0.09756   0.09055  -0.0428   1.0000   0.0685
  -9.000  -0.3783   0.09378   0.08687  -0.0440   1.0000   0.0684
  -8.750  -0.3865   0.09010   0.08330  -0.0449   1.0000   0.0684
  -8.500  -0.3990   0.08672   0.08005  -0.0451   1.0000   0.0684
  -8.250  -0.4133   0.08332   0.07678  -0.0454   1.0000   0.0683
  -8.000  -0.4270   0.07963   0.07318  -0.0458   1.0000   0.0681
  -7.750  -0.4410   0.07590   0.06950  -0.0457   1.0000   0.0680
  -7.500  -0.4542   0.07203   0.06564  -0.0455   1.0000   0.0679
  -7.250  -0.4654   0.06797   0.06152  -0.0453   1.0000   0.0678
  -7.000  -0.4736   0.06372   0.05716  -0.0452   1.0000   0.0677
  -6.750  -0.4779   0.05933   0.05256  -0.0453   1.0000   0.0676
  -6.500  -0.4771   0.05483   0.04776  -0.0456   0.9997   0.0677
  -6.250  -0.4518   0.04803   0.04013  -0.0512   0.9918   0.0695
  -6.000  -0.4208   0.04492   0.03676  -0.0545   0.9848   0.0722
  -5.750  -0.3899   0.04190   0.03336  -0.0572   0.9770   0.0741
  -5.500  -0.3576   0.03875   0.02969  -0.0598   0.9695   0.0760
  -5.250  -0.3222   0.03608   0.02643  -0.0624   0.9626   0.0798
  -5.000  -0.2895   0.03382   0.02361  -0.0641   0.9543   0.0839
  -4.750  -0.2517   0.03231   0.02195  -0.0666   0.9480   0.0874
  -4.500  -0.2199   0.03093   0.02031  -0.0677   0.9388   0.0915
  -4.250  -0.1801   0.02959   0.01868  -0.0700   0.9329   0.0982
  -4.000  -0.1490   0.02885   0.01785  -0.0709   0.9230   0.1072
  -3.750  -0.1083   0.02790   0.01679  -0.0733   0.9171   0.1198
  -3.500  -0.0769   0.02714   0.01591  -0.0740   0.9074   0.1374
  -3.250  -0.0365   0.02633   0.01509  -0.0765   0.9014   0.1703
  -3.000  -0.0076   0.02584   0.01469  -0.0771   0.8909   0.2077
  -2.750   0.0294   0.02533   0.01430  -0.0791   0.8843   0.2593
  -2.500   0.0572   0.02493   0.01397  -0.0792   0.8737   0.2950
  -2.250   0.0887   0.02441   0.01358  -0.0800   0.8653   0.3413
  -2.000   0.1179   0.02378   0.01330  -0.0803   0.8564   0.4098
  -1.750   0.1414   0.02303   0.01319  -0.0792   0.8470   0.5340
  -1.500   0.1716   0.02217   0.01320  -0.0773   0.8402   0.8053
  -1.250   0.2376   0.02199   0.01277  -0.0842   0.8337   1.0000
  -1.000   0.2655   0.02212   0.01261  -0.0843   0.8241   1.0000
  -0.750   0.2897   0.02235   0.01259  -0.0838   0.8135   1.0000
  -0.500   0.3216   0.02240   0.01238  -0.0844   0.8061   1.0000
  -0.250   0.3431   0.02272   0.01253  -0.0835   0.7949   1.0000
   0.000   0.3705   0.02289   0.01252  -0.0834   0.7863   1.0000
   0.250   0.3965   0.02311   0.01257  -0.0830   0.7770   1.0000
   0.500   0.4203   0.02341   0.01273  -0.0824   0.7672   1.0000
   0.750   0.4497   0.02351   0.01269  -0.0825   0.7596   1.0000
   1.000   0.4716   0.02388   0.01297  -0.0816   0.7489   1.0000
   1.250   0.5014   0.02394   0.01291  -0.0816   0.7414   1.0000
   1.500   0.5243   0.02424   0.01314  -0.0808   0.7306   1.0000
   1.750   0.5487   0.02448   0.01331  -0.0800   0.7203   1.0000
   2.000   0.5792   0.02443   0.01316  -0.0800   0.7121   1.0000
   2.250   0.6013   0.02474   0.01344  -0.0789   0.7002   1.0000
   2.500   0.6262   0.02492   0.01357  -0.0782   0.6895   1.0000
   2.750   0.6573   0.02478   0.01336  -0.0780   0.6808   1.0000
   3.000   0.6799   0.02504   0.01361  -0.0769   0.6682   1.0000
   3.250   0.7041   0.02521   0.01376  -0.0760   0.6560   1.0000
   3.500   0.7302   0.02528   0.01381  -0.0752   0.6440   1.0000
   3.750   0.7586   0.02523   0.01371  -0.0747   0.6326   1.0000
   4.000   0.7838   0.02534   0.01381  -0.0738   0.6196   1.0000
   4.250   0.8070   0.02557   0.01406  -0.0727   0.6057   1.0000
   4.500   0.8305   0.02578   0.01430  -0.0717   0.5917   1.0000
   4.750   0.8541   0.02600   0.01453  -0.0707   0.5775   1.0000
   5.000   0.8775   0.02623   0.01480  -0.0696   0.5630   1.0000
   5.250   0.9005   0.02648   0.01507  -0.0685   0.5479   1.0000
   5.500   0.9228   0.02676   0.01538  -0.0674   0.5322   1.0000
   5.750   0.9443   0.02706   0.01575  -0.0661   0.5159   1.0000
   6.000   0.9653   0.02741   0.01614  -0.0648   0.4990   1.0000
   6.250   0.9858   0.02778   0.01655  -0.0635   0.4817   1.0000
   6.500   1.0061   0.02816   0.01697  -0.0621   0.4640   1.0000
   6.750   1.0264   0.02857   0.01742  -0.0608   0.4467   1.0000
   7.000   1.0458   0.02905   0.01791  -0.0594   0.4292   1.0000
   7.250   1.0640   0.02965   0.01855  -0.0580   0.4116   1.0000
   7.500   1.0828   0.03026   0.01918  -0.0566   0.3955   1.0000
   7.750   1.1022   0.03092   0.01986  -0.0554   0.3811   1.0000
   8.000   1.1227   0.03159   0.02052  -0.0543   0.3683   1.0000
   8.250   1.1420   0.03240   0.02137  -0.0532   0.3560   1.0000
   8.500   1.1603   0.03332   0.02237  -0.0520   0.3445   1.0000
   8.750   1.1803   0.03420   0.02333  -0.0511   0.3345   1.0000
   9.000   1.2015   0.03508   0.02427  -0.0503   0.3255   1.0000
   9.250   1.2198   0.03622   0.02557  -0.0493   0.3174   1.0000
   9.500   1.2424   0.03716   0.02659  -0.0487   0.3102   1.0000
   9.750   1.2590   0.03843   0.02808  -0.0476   0.3030   1.0000
  10.000   1.2786   0.03954   0.02934  -0.0468   0.2961   1.0000
  10.250   1.2975   0.04078   0.03076  -0.0460   0.2901   1.0000
  10.500   1.3105   0.04229   0.03254  -0.0446   0.2840   1.0000
  10.750   1.3324   0.04320   0.03352  -0.0439   0.2767   1.0000
  11.000   1.3312   0.04492   0.03556  -0.0410   0.2689   1.0000
  11.250   1.3405   0.04591   0.03662  -0.0390   0.2596   1.0000
  11.500   1.3393   0.04734   0.03821  -0.0362   0.2503   1.0000
  11.750   1.3352   0.04910   0.04015  -0.0336   0.2414   1.0000
  12.000   1.3372   0.05025   0.04132  -0.0315   0.2307   1.0000
  12.250   1.3239   0.05290   0.04421  -0.0292   0.2219   1.0000
  12.500   1.3157   0.05525   0.04669  -0.0276   0.2123   1.0000
  12.750   1.3101   0.05734   0.04879  -0.0263   0.2016   1.0000
  13.000   1.2922   0.06146   0.05321  -0.0257   0.1933   1.0000
  13.250   1.2811   0.06488   0.05673  -0.0254   0.1835   1.0000
  13.500   1.2721   0.06814   0.06005  -0.0254   0.1729   1.0000
  13.750   1.2520   0.07379   0.06603  -0.0266   0.1645   1.0000
  14.000   1.2380   0.07854   0.07092  -0.0276   0.1545   1.0000
  14.250   1.2249   0.08337   0.07588  -0.0288   0.1437   1.0000
  14.500   1.2031   0.09032   0.08309  -0.0312   0.1346   1.0000
  14.750   1.1836   0.09707   0.08997  -0.0337   0.1249   1.0000
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