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GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 100,000
Max Cl/Cd: 45.3 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe769-il-100000-n5.txt
Download as CSV file: xf-goe769-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2362   0.11342   0.10832  -0.0231   1.0000   0.0761
  -9.500  -0.2360   0.11057   0.10554  -0.0249   1.0000   0.0762
  -9.250  -0.2357   0.10761   0.10265  -0.0266   1.0000   0.0763
  -9.000  -0.2340   0.10463   0.09974  -0.0279   1.0000   0.0764
  -8.750  -0.2315   0.10164   0.09683  -0.0289   1.0000   0.0764
  -8.250  -0.2274   0.09590   0.09127  -0.0301   1.0000   0.0764
  -8.000  -0.2096   0.08881   0.08415  -0.0341   0.9611   0.0622
  -7.500  -0.1678   0.07748   0.07262  -0.0485   0.8712   0.0561
  -7.250  -0.1513   0.07418   0.06920  -0.0514   0.8363   0.0554
  -7.000  -0.1467   0.07094   0.06585  -0.0535   0.8081   0.0547
  -6.750  -0.1434   0.06713   0.06194  -0.0564   0.7862   0.0540
  -6.500  -0.1413   0.06256   0.05725  -0.0601   0.7685   0.0532
  -6.250  -0.1401   0.05673   0.05123  -0.0648   0.7541   0.0523
  -6.000  -0.1384   0.04977   0.04398  -0.0693   0.7413   0.0518
  -5.750  -0.1268   0.04576   0.03971  -0.0709   0.7285   0.0524
  -5.500  -0.1144   0.04143   0.03503  -0.0723   0.7168   0.0532
  -5.250  -0.1014   0.03685   0.02997  -0.0732   0.7054   0.0539
  -5.000  -0.0856   0.03299   0.02553  -0.0732   0.6949   0.0544
  -4.750  -0.0666   0.03000   0.02200  -0.0729   0.6833   0.0550
  -4.500  -0.0454   0.02752   0.01890  -0.0722   0.6730   0.0560
  -4.250  -0.0215   0.02633   0.01750  -0.0715   0.6605   0.0569
  -4.000   0.0034   0.02569   0.01672  -0.0709   0.6496   0.0584
  -3.750   0.0283   0.02477   0.01558  -0.0702   0.6376   0.0605
  -3.500   0.0536   0.02362   0.01406  -0.0694   0.6271   0.0626
  -3.250   0.0792   0.02307   0.01346  -0.0688   0.6151   0.0641
  -3.000   0.1051   0.02241   0.01266  -0.0681   0.6040   0.0660
  -2.750   0.1313   0.02164   0.01163  -0.0673   0.5928   0.0688
  -2.500   0.1573   0.02131   0.01133  -0.0667   0.5813   0.0717
  -2.250   0.1837   0.02084   0.01064  -0.0659   0.5705   0.0763
  -2.000   0.2096   0.02051   0.01036  -0.0653   0.5580   0.0800
  -1.750   0.2358   0.02010   0.00981  -0.0645   0.5470   0.0855
  -1.500   0.2618   0.01984   0.00952  -0.0638   0.5341   0.0923
  -1.250   0.2877   0.01958   0.00924  -0.0631   0.5215   0.0998
  -1.000   0.3135   0.01935   0.00892  -0.0624   0.5104   0.1090
  -0.750   0.3394   0.01915   0.00872  -0.0617   0.4978   0.1197
  -0.500   0.3653   0.01898   0.00850  -0.0610   0.4873   0.1316
  -0.250   0.3912   0.01885   0.00831  -0.0603   0.4765   0.1443
   0.000   0.4168   0.01869   0.00817  -0.0596   0.4665   0.1575
   0.250   0.4424   0.01855   0.00803  -0.0588   0.4568   0.1721
   0.500   0.4682   0.01844   0.00795  -0.0582   0.4471   0.1899
   0.750   0.4942   0.01836   0.00787  -0.0576   0.4378   0.2149
   1.000   0.5206   0.01823   0.00788  -0.0571   0.4287   0.2580
   1.250   0.5459   0.01796   0.00789  -0.0565   0.4198   0.3554
   1.750   0.6281   0.01684   0.00801  -0.0606   0.3998   1.0000
   2.000   0.6526   0.01710   0.00811  -0.0597   0.3914   1.0000
   2.250   0.6770   0.01736   0.00822  -0.0588   0.3830   1.0000
   2.500   0.7014   0.01764   0.00834  -0.0580   0.3753   1.0000
   2.750   0.7257   0.01792   0.00852  -0.0571   0.3669   1.0000
   3.250   0.7741   0.01853   0.00890  -0.0554   0.3514   1.0000
   3.500   0.7980   0.01884   0.00907  -0.0546   0.3440   1.0000
   3.750   0.8220   0.01918   0.00933  -0.0537   0.3366   1.0000
   4.000   0.8458   0.01951   0.00960  -0.0529   0.3292   1.0000
   4.250   0.8695   0.01988   0.00980  -0.0520   0.3229   1.0000
   4.500   0.8930   0.02024   0.01018  -0.0512   0.3152   1.0000
   4.750   0.9162   0.02061   0.01045  -0.0503   0.3087   1.0000
   5.000   0.9394   0.02103   0.01079  -0.0495   0.3026   1.0000
   5.250   0.9624   0.02144   0.01119  -0.0486   0.2959   1.0000
   5.500   0.9851   0.02185   0.01150  -0.0477   0.2904   1.0000
   5.750   1.0077   0.02231   0.01194  -0.0468   0.2847   1.0000
   6.000   1.0299   0.02277   0.01239  -0.0459   0.2788   1.0000
   6.250   1.0519   0.02322   0.01275  -0.0450   0.2740   1.0000
   6.500   1.0738   0.02374   0.01325  -0.0441   0.2691   1.0000
   6.750   1.0951   0.02426   0.01380  -0.0431   0.2639   1.0000
   7.000   1.1161   0.02476   0.01425  -0.0421   0.2594   1.0000
   7.250   1.1374   0.02529   0.01468  -0.0412   0.2555   1.0000
   7.500   1.1573   0.02591   0.01539  -0.0401   0.2509   1.0000
   7.750   1.1771   0.02651   0.01600  -0.0391   0.2467   1.0000
   8.000   1.1968   0.02708   0.01653  -0.0380   0.2430   1.0000
   8.250   1.2169   0.02769   0.01706  -0.0370   0.2397   1.0000
   8.500   1.2341   0.02843   0.01791  -0.0357   0.2357   1.0000
   8.750   1.2516   0.02914   0.01867  -0.0345   0.2321   1.0000
   9.000   1.2692   0.02982   0.01935  -0.0333   0.2288   1.0000
   9.250   1.2877   0.03048   0.01995  -0.0322   0.2260   1.0000
   9.500   1.3037   0.03131   0.02081  -0.0309   0.2231   1.0000
   9.750   1.3157   0.03223   0.02186  -0.0292   0.2197   1.0000
  10.000   1.3272   0.03310   0.02280  -0.0274   0.2167   1.0000
  10.250   1.3399   0.03394   0.02365  -0.0258   0.2140   1.0000
  10.500   1.3543   0.03476   0.02445  -0.0244   0.2117   1.0000
  10.750   1.3713   0.03560   0.02524  -0.0234   0.2094   1.0000
  11.000   1.3737   0.03699   0.02683  -0.0212   0.2069   1.0000
  11.250   1.3775   0.03842   0.02839  -0.0195   0.2042   1.0000
  11.500   1.3832   0.03981   0.02988  -0.0181   0.2017   1.0000
  11.750   1.3912   0.04112   0.03124  -0.0169   0.1993   1.0000
  12.000   1.4027   0.04229   0.03242  -0.0160   0.1972   1.0000
  12.250   1.4194   0.04324   0.03332  -0.0154   0.1954   1.0000
  12.500   1.4148   0.04560   0.03588  -0.0143   0.1934   1.0000
  12.750   1.4042   0.04861   0.03912  -0.0136   0.1912   1.0000
  13.000   1.3942   0.05182   0.04251  -0.0133   0.1890   1.0000
  13.250   1.3870   0.05497   0.04580  -0.0133   0.1868   1.0000
  13.500   1.3862   0.05758   0.04850  -0.0133   0.1847   1.0000
  13.750   1.3950   0.05928   0.05022  -0.0131   0.1829   1.0000
  14.000   1.4139   0.05999   0.05087  -0.0126   0.1812   1.0000
  14.250   1.3534   0.06975   0.06104  -0.0158   0.1789   1.0000
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