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GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 200,000
Max Cl/Cd: 59.05 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe769-il-200000.txt
Download as CSV file: xf-goe769-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 769 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2179   0.10426   0.10075  -0.0219   1.0000   0.0654
  -9.000  -0.2185   0.10151   0.09805  -0.0238   1.0000   0.0676
  -8.750  -0.2368   0.09800   0.09463  -0.0286   1.0000   0.0688
  -8.500  -0.2196   0.09534   0.09202  -0.0267   1.0000   0.0693
  -8.250  -0.2087   0.09300   0.08975  -0.0258   1.0000   0.0700
  -8.000  -0.2027   0.09075   0.08758  -0.0256   1.0000   0.0709
  -7.750  -0.1887   0.08755   0.08446  -0.0286   0.9837   0.0726
  -7.500  -0.1716   0.07938   0.07620  -0.0494   0.9177   0.0762
  -7.250  -0.1234   0.07587   0.07257  -0.0518   0.8815   0.0772
  -7.000  -0.0999   0.07308   0.06960  -0.0543   0.8410   0.0786
  -6.750  -0.0957   0.07074   0.06713  -0.0549   0.8107   0.0801
  -6.500  -0.1281   0.06407   0.06021  -0.0677   0.7890   0.0842
  -6.250  -0.1118   0.06225   0.05835  -0.0652   0.7723   0.0847
  -6.000  -0.0966   0.06067   0.05670  -0.0632   0.7567   0.0855
  -5.750  -0.0825   0.05895   0.05494  -0.0624   0.7414   0.0870
  -5.500  -0.0827   0.05256   0.04812  -0.0710   0.7313   0.0937
  -5.250  -0.0652   0.05074   0.04632  -0.0695   0.7176   0.0944
  -5.000  -0.0480   0.04900   0.04455  -0.0686   0.7048   0.0954
  -4.750  -0.0536   0.03223   0.02637  -0.0742   0.7014   0.0690
  -4.500  -0.0324   0.03011   0.02405  -0.0735   0.6904   0.0673
  -4.250  -0.0126   0.02719   0.02076  -0.0728   0.6789   0.0659
  -4.000   0.0088   0.02467   0.01773  -0.0719   0.6684   0.0661
  -3.750   0.0320   0.02278   0.01542  -0.0709   0.6565   0.0668
  -3.500   0.0565   0.02125   0.01349  -0.0700   0.6448   0.0675
  -3.250   0.0820   0.02009   0.01189  -0.0690   0.6333   0.0684
  -3.000   0.1078   0.01919   0.01095  -0.0684   0.6206   0.0698
  -2.750   0.1341   0.01868   0.01032  -0.0676   0.6087   0.0716
  -2.500   0.1605   0.01813   0.00960  -0.0668   0.5947   0.0746
  -2.250   0.1868   0.01758   0.00897  -0.0661   0.5813   0.0777
  -2.000   0.2134   0.01723   0.00850  -0.0654   0.5693   0.0813
  -1.750   0.2400   0.01668   0.00789  -0.0647   0.5560   0.0855
  -1.500   0.2667   0.01642   0.00758  -0.0640   0.5442   0.0912
  -1.250   0.2931   0.01611   0.00726  -0.0633   0.5327   0.0985
  -1.000   0.3196   0.01580   0.00696  -0.0627   0.5208   0.1079
  -0.750   0.3460   0.01558   0.00665  -0.0620   0.5104   0.1190
  -0.500   0.3725   0.01535   0.00645  -0.0614   0.4987   0.1313
  -0.250   0.3991   0.01527   0.00630  -0.0608   0.4885   0.1442
   0.000   0.4252   0.01508   0.00614  -0.0602   0.4780   0.1583
   0.250   0.4512   0.01492   0.00602  -0.0595   0.4682   0.1739
   0.500   0.4772   0.01478   0.00589  -0.0589   0.4584   0.1919
   0.750   0.5032   0.01468   0.00584  -0.0582   0.4491   0.2153
   1.000   0.5284   0.01445   0.00580  -0.0575   0.4400   0.2610
   1.250   0.5457   0.01340   0.00587  -0.0556   0.4322   0.5764
   1.500   0.6197   0.01280   0.00586  -0.0638   0.4185   1.0000
   1.750   0.6444   0.01298   0.00595  -0.0629   0.4094   1.0000
   2.000   0.6690   0.01321   0.00600  -0.0620   0.4011   1.0000
   2.250   0.6937   0.01344   0.00614  -0.0611   0.3923   1.0000
   2.500   0.7183   0.01365   0.00622  -0.0602   0.3836   1.0000
   2.750   0.7429   0.01391   0.00638  -0.0594   0.3750   1.0000
   3.000   0.7675   0.01413   0.00650  -0.0585   0.3663   1.0000
   3.250   0.7922   0.01443   0.00668  -0.0577   0.3583   1.0000
   3.500   0.8167   0.01465   0.00685  -0.0568   0.3496   1.0000
   3.750   0.8412   0.01499   0.00704  -0.0560   0.3418   1.0000
   4.000   0.8655   0.01521   0.00725  -0.0552   0.3332   1.0000
   4.250   0.8900   0.01560   0.00745  -0.0544   0.3261   1.0000
   4.500   0.9141   0.01585   0.00774  -0.0536   0.3184   1.0000
   4.750   0.9384   0.01615   0.00794  -0.0528   0.3115   1.0000
   5.000   0.9626   0.01653   0.00826  -0.0520   0.3048   1.0000
   5.250   0.9866   0.01682   0.00853  -0.0512   0.2980   1.0000
   5.500   1.0108   0.01724   0.00880  -0.0505   0.2924   1.0000
   5.750   1.0345   0.01759   0.00919  -0.0497   0.2865   1.0000
   6.000   1.0582   0.01792   0.00949  -0.0489   0.2808   1.0000
   6.250   1.0822   0.01836   0.00980  -0.0482   0.2758   1.0000
   6.500   1.1054   0.01876   0.01025  -0.0473   0.2707   1.0000
   6.750   1.1287   0.01914   0.01063  -0.0465   0.2658   1.0000
   7.000   1.1521   0.01955   0.01097  -0.0458   0.2615   1.0000
   7.250   1.1756   0.02011   0.01146  -0.0451   0.2572   1.0000
   7.500   1.1975   0.02051   0.01194  -0.0441   0.2527   1.0000
   7.750   1.2200   0.02093   0.01235  -0.0433   0.2485   1.0000
   8.000   1.2432   0.02143   0.01278  -0.0426   0.2449   1.0000
   8.250   1.2661   0.02208   0.01341  -0.0419   0.2413   1.0000
   8.500   1.2866   0.02258   0.01400  -0.0409   0.2376   1.0000
   8.750   1.3077   0.02306   0.01450  -0.0399   0.2339   1.0000
   9.000   1.3297   0.02357   0.01496  -0.0391   0.2305   1.0000
   9.250   1.3544   0.02439   0.01567  -0.0388   0.2271   1.0000
   9.500   1.3718   0.02496   0.01640  -0.0374   0.2243   1.0000
   9.750   1.3903   0.02558   0.01710  -0.0362   0.2212   1.0000
  10.000   1.4099   0.02616   0.01771  -0.0352   0.2181   1.0000
  10.250   1.4310   0.02676   0.01827  -0.0344   0.2153   1.0000
  10.500   1.4566   0.02773   0.01912  -0.0344   0.2121   1.0000
  10.750   1.4688   0.02842   0.02000  -0.0325   0.2098   1.0000
  11.000   1.4826   0.02918   0.02089  -0.0308   0.2072   1.0000
  11.250   1.4980   0.02992   0.02171  -0.0294   0.2046   1.0000
  11.500   1.5154   0.03063   0.02243  -0.0282   0.2022   1.0000
  11.750   1.5365   0.03135   0.02311  -0.0276   0.1999   1.0000
  12.000   1.5592   0.03252   0.02424  -0.0275   0.1972   1.0000
  12.250   1.5610   0.03342   0.02533  -0.0244   0.1955   1.0000
  12.500   1.5632   0.03444   0.02650  -0.0215   0.1934   1.0000
  12.750   1.5685   0.03551   0.02770  -0.0193   0.1914   1.0000
  13.000   1.5771   0.03655   0.02881  -0.0176   0.1894   1.0000
  13.250   1.5902   0.03750   0.02979  -0.0165   0.1875   1.0000
  13.500   1.6098   0.03836   0.03061  -0.0160   0.1857   1.0000
  13.750   1.6338   0.03972   0.03194  -0.0161   0.1834   1.0000
  14.000   1.6228   0.04147   0.03392  -0.0133   0.1822   1.0000
  14.250   1.6124   0.04355   0.03620  -0.0113   0.1806   1.0000
  14.500   1.6026   0.04593   0.03877  -0.0098   0.1789   1.0000
  14.750   1.5950   0.04844   0.04144  -0.0089   0.1773   1.0000
  15.000   1.5907   0.05091   0.04404  -0.0083   0.1758   1.0000
  15.250   1.5931   0.05296   0.04617  -0.0080   0.1742   1.0000
  15.500   1.6048   0.05437   0.04759  -0.0076   0.1727   1.0000
  15.750   1.6296   0.05503   0.04819  -0.0073   0.1712   1.0000
  16.000   1.6184   0.05870   0.05202  -0.0072   0.1698   1.0000
  16.250   1.5567   0.06706   0.06076  -0.0090   0.1687   1.0000
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