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GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 506 AIRFOIL (goe506-il)
Reynolds number: 100,000
Max Cl/Cd: 45.09 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe506-il-100000.txt
Download as CSV file: xf-goe506-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 506 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4414   0.11260   0.10884  -0.0152   1.0000   0.1743
  -7.750  -0.5055   0.11083   0.10722  -0.0165   1.0000   0.1796
  -7.000  -0.6980   0.06024   0.05536  -0.0320   1.0000   0.0857
  -6.750  -0.6939   0.05570   0.05051  -0.0303   1.0000   0.0800
  -6.500  -0.7019   0.04859   0.04206  -0.0274   1.0000   0.0727
  -6.250  -0.6906   0.04640   0.03940  -0.0253   1.0000   0.0721
  -6.000  -0.6788   0.04370   0.03637  -0.0235   1.0000   0.0725
  -5.750  -0.6648   0.04149   0.03381  -0.0217   1.0000   0.0726
  -5.500  -0.6495   0.03957   0.03157  -0.0200   1.0000   0.0727
  -5.250  -0.6329   0.03792   0.02964  -0.0184   1.0000   0.0728
  -5.000  -0.6156   0.03638   0.02794  -0.0170   1.0000   0.0737
  -4.750  -0.5983   0.03524   0.02670  -0.0157   1.0000   0.0758
  -4.500  -0.5805   0.03432   0.02566  -0.0143   1.0000   0.0778
  -4.250  -0.4473   0.03529   0.02622  -0.0322   0.9469   0.0849
  -4.000  -0.3887   0.03458   0.02563  -0.0372   0.9256   0.0909
  -3.750  -0.3446   0.03408   0.02501  -0.0396   0.9101   0.0969
  -3.500  -0.3000   0.03330   0.02427  -0.0422   0.8963   0.1100
  -3.250  -0.2727   0.03232   0.02358  -0.0418   0.8828   0.1335
  -3.000  -0.2437   0.03195   0.02373  -0.0417   0.8705   0.2553
  -2.750  -0.2047   0.03246   0.02420  -0.0433   0.8619   0.3157
  -2.500  -0.1786   0.03254   0.02420  -0.0428   0.8515   0.3397
  -2.250  -0.1523   0.03260   0.02422  -0.0423   0.8411   0.3644
  -2.000  -0.1086   0.03245   0.02407  -0.0446   0.8338   0.3883
  -1.750  -0.0849   0.03220   0.02380  -0.0438   0.8221   0.4028
  -1.500  -0.0416   0.03184   0.02342  -0.0460   0.8157   0.4259
  -1.250  -0.0143   0.03143   0.02306  -0.0456   0.8047   0.4475
  -1.000   0.0142   0.03095   0.02268  -0.0453   0.7939   0.4690
  -0.750   0.0618   0.03008   0.02192  -0.0481   0.7881   0.4994
  -0.500   0.0892   0.02941   0.02148  -0.0476   0.7763   0.5370
  -0.250   0.3090   0.02770   0.02122  -0.0828   0.7799   1.0000
   0.000   0.3561   0.02675   0.02000  -0.0854   0.7736   1.0000
   0.250   0.3806   0.02616   0.01925  -0.0842   0.7614   1.0000
   0.500   0.4345   0.02486   0.01778  -0.0875   0.7573   1.0000
   1.000   0.5125   0.02271   0.01538  -0.0892   0.7385   1.0000
   1.250   0.5524   0.02160   0.01416  -0.0902   0.7261   1.0000
   1.500   0.5923   0.02051   0.01296  -0.0912   0.7103   1.0000
   1.750   0.6128   0.01984   0.01218  -0.0889   0.6861   1.0000
   2.000   0.6472   0.01905   0.01120  -0.0891   0.6582   1.0000
   2.250   0.6730   0.01862   0.01055  -0.0879   0.6237   1.0000
   2.500   0.7101   0.01830   0.00990  -0.0891   0.5904   1.0000
   2.750   0.7489   0.01835   0.00955  -0.0909   0.5634   1.0000
   3.000   0.7837   0.01866   0.00954  -0.0923   0.5425   1.0000
   3.250   0.8156   0.01907   0.00969  -0.0932   0.5263   1.0000
   3.500   0.8454   0.01952   0.00995  -0.0938   0.5133   1.0000
   3.750   0.8782   0.02000   0.01022  -0.0950   0.5026   1.0000
   4.000   0.9027   0.02046   0.01060  -0.0947   0.4933   1.0000
   4.250   0.9311   0.02096   0.01099  -0.0951   0.4852   1.0000
   4.500   0.9535   0.02142   0.01141  -0.0943   0.4775   1.0000
   4.750   0.9852   0.02194   0.01179  -0.0954   0.4710   1.0000
   5.000   1.0022   0.02241   0.01233  -0.0936   0.4651   1.0000
   5.250   1.0281   0.02290   0.01277  -0.0935   0.4595   1.0000
   5.500   1.0570   0.02344   0.01324  -0.0941   0.4543   1.0000
   5.750   1.0715   0.02394   0.01384  -0.0919   0.4491   1.0000
   6.000   1.0941   0.02446   0.01437  -0.0912   0.4444   1.0000
   6.250   1.1254   0.02502   0.01486  -0.0922   0.4401   1.0000
   6.500   1.1403   0.02559   0.01553  -0.0901   0.4357   1.0000
   6.750   1.1552   0.02614   0.01618  -0.0881   0.4309   1.0000
   7.000   1.1796   0.02665   0.01669  -0.0878   0.4260   1.0000
   7.250   1.2044   0.02725   0.01729  -0.0876   0.4215   1.0000
   7.500   1.2129   0.02786   0.01806  -0.0844   0.4167   1.0000
   7.750   1.2314   0.02841   0.01866  -0.0830   0.4118   1.0000
   8.000   1.2658   0.02898   0.01916  -0.0846   0.4072   1.0000
   8.250   1.2701   0.02971   0.02009  -0.0808   0.4028   1.0000
   8.500   1.2815   0.03034   0.02086  -0.0782   0.3977   1.0000
   8.750   1.3099   0.03086   0.02136  -0.0786   0.3926   1.0000
   9.000   1.3209   0.03164   0.02226  -0.0761   0.3876   1.0000
   9.250   1.3267   0.03236   0.02314  -0.0727   0.3821   1.0000
   9.500   1.3595   0.03282   0.02356  -0.0738   0.3760   1.0000
   9.750   1.3584   0.03372   0.02465  -0.0693   0.3703   1.0000
  10.000   1.3664   0.03436   0.02538  -0.0662   0.3638   1.0000
  10.250   1.3919   0.03494   0.02596  -0.0662   0.3567   1.0000
  10.500   1.3804   0.03572   0.02690  -0.0599   0.3498   1.0000
  10.750   1.4079   0.03589   0.02697  -0.0600   0.3409   1.0000
  11.000   1.3924   0.03679   0.02806  -0.0535   0.3339   1.0000
  11.250   1.4161   0.03678   0.02793  -0.0529   0.3248   1.0000
  11.500   1.4003   0.03789   0.02925  -0.0468   0.3180   1.0000
  11.750   1.4291   0.03776   0.02897  -0.0471   0.3097   1.0000
  12.000   1.4072   0.03930   0.03080  -0.0407   0.3037   1.0000
  12.250   1.4217   0.03956   0.03105  -0.0391   0.2969   1.0000
  12.500   1.4173   0.04066   0.03228  -0.0354   0.2907   1.0000
  12.750   1.4093   0.04186   0.03363  -0.0315   0.2844   1.0000
  13.000   1.4318   0.04177   0.03346  -0.0309   0.2782   1.0000
  13.250   1.4080   0.04410   0.03610  -0.0259   0.2730   1.0000
  13.500   1.4087   0.04482   0.03689  -0.0233   0.2665   1.0000
  13.750   1.4048   0.04613   0.03831  -0.0207   0.2607   1.0000
  14.000   1.3908   0.04844   0.04084  -0.0177   0.2554   1.0000
  14.250   1.4006   0.04868   0.04107  -0.0162   0.2492   1.0000
  14.500   1.3801   0.05199   0.04465  -0.0135   0.2444   1.0000
  14.750   1.3704   0.05423   0.04703  -0.0116   0.2378   1.0000
  15.000   1.3586   0.05695   0.04989  -0.0100   0.2314   1.0000
  15.250   1.3426   0.06057   0.05368  -0.0088   0.2255   1.0000
  15.500   1.3369   0.06323   0.05642  -0.0080   0.2192   1.0000
  15.750   1.3113   0.06866   0.06206  -0.0077   0.2137   1.0000
  16.000   1.3029   0.07208   0.06551  -0.0077   0.2061   1.0000
  16.250   1.2738   0.07885   0.07248  -0.0086   0.2023   1.0000
  16.500   1.2675   0.08239   0.07599  -0.0092   0.1930   1.0000
  16.750   1.2373   0.08992   0.08369  -0.0109   0.1896   1.0000
  17.000   1.2344   0.09316   0.08688  -0.0116   0.1789   1.0000
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