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GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 7K AIRFOIL (goe07k-il)
Reynolds number: 100,000
Max Cl/Cd: 40.69 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe07k-il-100000-n5.txt
Download as CSV file: xf-goe07k-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 7K 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3071   0.10283   0.09798  -0.0731   0.9492   0.0462
  -8.000  -0.3095   0.09938   0.09457  -0.0780   0.9454   0.0470
  -7.750  -0.3190   0.09710   0.09233  -0.0763   0.9395   0.0469
  -7.250  -0.3147   0.08797   0.08318  -0.0776   0.9323   0.0329
  -7.000  -0.3200   0.08483   0.08005  -0.0773   0.9265   0.0313
  -6.750  -0.3220   0.08063   0.07584  -0.0786   0.9210   0.0296
  -6.500  -0.3145   0.07488   0.07000  -0.0829   0.9173   0.0275
  -6.000  -0.3085   0.06419   0.05889  -0.0846   0.9054   0.0240
  -5.750  -0.2959   0.05964   0.05411  -0.0856   0.9028   0.0239
  -5.500  -0.2939   0.05632   0.05058  -0.0834   0.8979   0.0240
  -5.250  -0.2896   0.05243   0.04643  -0.0816   0.8931   0.0245
  -5.000  -0.2771   0.04902   0.04277  -0.0812   0.8902   0.0255
  -4.750  -0.2588   0.04549   0.03885  -0.0808   0.8881   0.0257
  -4.500  -0.2509   0.04301   0.03604  -0.0779   0.8841   0.0261
  -4.250  -0.2411   0.04068   0.03332  -0.0750   0.8801   0.0262
  -4.000  -0.2232   0.03887   0.03118  -0.0737   0.8774   0.0276
  -3.750  -0.2011   0.03703   0.02894  -0.0728   0.8753   0.0297
  -3.500  -0.1766   0.03473   0.02606  -0.0718   0.8737   0.0317
  -3.250  -0.1581   0.03307   0.02389  -0.0696   0.8708   0.0337
  -3.000  -0.1444   0.03209   0.02249  -0.0666   0.8667   0.0364
  -2.750  -0.1235   0.03116   0.02144  -0.0656   0.8641   0.0396
  -2.500  -0.0984   0.03046   0.02048  -0.0650   0.8621   0.0454
  -2.250  -0.0713   0.02951   0.01936  -0.0649   0.8605   0.0515
  -2.000  -0.0425   0.02895   0.01857  -0.0650   0.8591   0.0601
  -1.750  -0.0312   0.02859   0.01828  -0.0623   0.8546   0.0678
  -1.500  -0.0145   0.02829   0.01791  -0.0604   0.8512   0.0761
  -1.250   0.0078   0.02802   0.01757  -0.0595   0.8487   0.0854
  -1.000   0.0335   0.02772   0.01722  -0.0593   0.8467   0.0965
  -0.750   0.0623   0.02750   0.01688  -0.0596   0.8451   0.1067
  -0.500   0.2124   0.02566   0.01779  -0.0880   0.8520   1.0000
  -0.250   0.2354   0.02590   0.01779  -0.0874   0.8489   1.0000
   0.000   0.2614   0.02611   0.01780  -0.0873   0.8467   1.0000
   0.250   0.2899   0.02630   0.01780  -0.0877   0.8450   1.0000
   0.500   0.3008   0.02676   0.01816  -0.0850   0.8396   1.0000
   0.750   0.3198   0.02711   0.01838  -0.0837   0.8357   1.0000
   1.000   0.3458   0.02733   0.01849  -0.0837   0.8330   1.0000
   1.250   0.3751   0.02749   0.01855  -0.0843   0.8310   1.0000
   1.750   0.4109   0.02813   0.01907  -0.0812   0.8204   1.0000
   2.000   0.4412   0.02818   0.01906  -0.0819   0.8175   1.0000
   2.250   0.4752   0.02814   0.01899  -0.0832   0.8155   1.0000
   2.500   0.4808   0.02873   0.01957  -0.0795   0.8068   1.0000
   2.750   0.5100   0.02879   0.01963  -0.0800   0.8036   1.0000
   3.000   0.5431   0.02875   0.01960  -0.0811   0.8014   1.0000
   3.250   0.5505   0.02935   0.02022  -0.0778   0.7927   1.0000
   3.500   0.5795   0.02940   0.02030  -0.0782   0.7892   1.0000
   3.750   0.6120   0.02935   0.02031  -0.0792   0.7869   1.0000
   4.000   0.6205   0.02995   0.02096  -0.0762   0.7778   1.0000
   4.250   0.6501   0.02994   0.02105  -0.0766   0.7743   1.0000
   4.500   0.6835   0.02980   0.02100  -0.0776   0.7719   1.0000
   4.750   0.6917   0.03045   0.02173  -0.0746   0.7618   1.0000
   5.000   0.7233   0.03031   0.02173  -0.0752   0.7585   1.0000
   5.250   0.7377   0.03072   0.02224  -0.0732   0.7494   1.0000
   5.500   0.7699   0.03034   0.02203  -0.0737   0.7444   1.0000
   5.750   0.7885   0.03040   0.02222  -0.0720   0.7343   1.0000
   7.250   0.9195   0.02735   0.02023  -0.0614   0.6300   1.0000
   7.500   0.9765   0.02400   0.01540  -0.0613   0.3844   1.0000
   7.750   0.9659   0.02605   0.01656  -0.0555   0.2506   1.0000
   8.000   0.9648   0.02790   0.01776  -0.0517   0.1468   1.0000
   8.250   0.9660   0.02977   0.01907  -0.0482   0.0764   1.0000
   8.500   0.9727   0.03126   0.02048  -0.0453   0.0516   1.0000
   8.750   0.9810   0.03261   0.02184  -0.0426   0.0409   1.0000
   9.000   0.9890   0.03398   0.02325  -0.0400   0.0348   1.0000
   9.250   0.9975   0.03533   0.02476  -0.0375   0.0312   1.0000
   9.500   1.0049   0.03680   0.02631  -0.0350   0.0282   1.0000
   9.750   1.0106   0.03859   0.02816  -0.0324   0.0258   1.0000
  10.000   1.0231   0.04006   0.02983  -0.0304   0.0241   1.0000
  10.250   1.0385   0.04152   0.03144  -0.0288   0.0222   1.0000
  10.500   1.0543   0.04301   0.03302  -0.0275   0.0204   1.0000
  10.750   1.0754   0.04489   0.03498  -0.0268   0.0191   1.0000
  11.000   1.1096   0.04764   0.03796  -0.0274   0.0182   1.0000
  11.250   1.1275   0.04982   0.04055  -0.0261   0.0173   1.0000
  11.500   1.1408   0.05242   0.04354  -0.0244   0.0164   1.0000
  11.750   1.1470   0.05490   0.04632  -0.0222   0.0157   1.0000
  12.000   1.1497   0.05776   0.04950  -0.0196   0.0153   1.0000
  12.250   1.1477   0.06081   0.05289  -0.0169   0.0152   1.0000
  12.500   1.1414   0.06405   0.05645  -0.0139   0.0151   1.0000
  12.750   1.1320   0.06741   0.06010  -0.0110   0.0150   1.0000
  13.000   1.1182   0.07120   0.06423  -0.0082   0.0151   1.0000
  13.250   1.1027   0.07507   0.06837  -0.0058   0.0150   1.0000
  13.500   1.0852   0.07926   0.07283  -0.0038   0.0150   1.0000
  13.750   1.0657   0.08382   0.07765  -0.0024   0.0151   1.0000
  14.000   1.0441   0.08893   0.08301  -0.0018   0.0152   1.0000
  14.250   1.0216   0.09454   0.08884  -0.0020   0.0153   1.0000
  14.500   0.9990   0.10066   0.09517  -0.0033   0.0154   1.0000
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