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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 100,000
Max Cl/Cd: 54.07 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe314-il-100000-n5.txt
Download as CSV file: xf-goe314-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3034   0.09562   0.09068  -0.0240   1.0000   0.0503
  -7.750  -0.3055   0.09355   0.08868  -0.0243   1.0000   0.0514
  -7.500  -0.3125   0.09197   0.08720  -0.0246   1.0000   0.0522
  -7.250  -0.3167   0.09025   0.08556  -0.0271   1.0000   0.0527
  -7.000  -0.3175   0.08833   0.08369  -0.0302   1.0000   0.0530
  -6.750  -0.3159   0.08623   0.08160  -0.0327   1.0000   0.0532
  -6.500  -0.3147   0.08263   0.07809  -0.0307   1.0000   0.0536
  -6.250  -0.3139   0.07941   0.07497  -0.0262   1.0000   0.0545
  -6.000  -0.3030   0.07642   0.07199  -0.0263   0.9971   0.0559
  -5.750  -0.2735   0.07241   0.06793  -0.0320   0.9880   0.0580
  -5.500  -0.2416   0.06841   0.06383  -0.0389   0.9776   0.0605
  -5.250  -0.1891   0.06531   0.06024  -0.0530   0.9637   0.0636
  -5.000  -0.1700   0.06029   0.05532  -0.0542   0.9546   0.0645
  -4.750  -0.1464   0.05671   0.05178  -0.0555   0.9470   0.0667
  -4.500  -0.1179   0.05376   0.04875  -0.0585   0.9354   0.0704
  -4.000  -0.0443   0.04729   0.04176  -0.0680   0.9142   0.0770
  -3.750  -0.0175   0.04439   0.03882  -0.0695   0.9024   0.0791
  -3.500   0.0130   0.04194   0.03623  -0.0716   0.8897   0.0827
  -3.250   0.0507   0.03986   0.03371  -0.0746   0.8768   0.0896
  -3.000   0.0771   0.03725   0.03112  -0.0756   0.8637   0.0937
  -2.750   0.1116   0.03568   0.02913  -0.0773   0.8496   0.1030
  -2.500   0.1386   0.03333   0.02672  -0.0780   0.8345   0.1053
  -2.250   0.1770   0.02976   0.02241  -0.0781   0.8203   0.0619
  -2.000   0.2045   0.02794   0.02036  -0.0781   0.8039   0.0599
  -1.750   0.2322   0.02632   0.01843  -0.0777   0.7864   0.0581
  -1.500   0.2591   0.02508   0.01691  -0.0772   0.7677   0.0590
  -1.250   0.2861   0.02397   0.01552  -0.0766   0.7483   0.0603
  -1.000   0.3131   0.02284   0.01409  -0.0760   0.7279   0.0598
  -0.750   0.3401   0.02181   0.01275  -0.0753   0.7071   0.0592
  -0.500   0.3664   0.02093   0.01160  -0.0745   0.6844   0.0591
  -0.250   0.3929   0.02015   0.01055  -0.0737   0.6618   0.0592
   0.000   0.4192   0.01949   0.00963  -0.0729   0.6389   0.0597
   0.250   0.4454   0.01899   0.00888  -0.0721   0.6167   0.0615
   0.500   0.4714   0.01863   0.00826  -0.0713   0.5962   0.0640
   0.750   0.4968   0.01812   0.00766  -0.0706   0.5768   0.0656
   1.000   0.5222   0.01777   0.00721  -0.0698   0.5593   0.0670
   1.250   0.5475   0.01750   0.00684  -0.0691   0.5433   0.0687
   1.500   0.5724   0.01729   0.00654  -0.0683   0.5288   0.0709
   1.750   0.5976   0.01720   0.00631  -0.0675   0.5153   0.0750
   2.000   0.6231   0.01710   0.00619  -0.0669   0.5020   0.0807
   2.250   0.6486   0.01710   0.00607  -0.0663   0.4890   0.0857
   2.500   0.6739   0.01712   0.00598  -0.0656   0.4760   0.0918
   2.750   0.6990   0.01718   0.00596  -0.0650   0.4638   0.1056
   3.000   0.7241   0.01720   0.00596  -0.0643   0.4521   0.1299
   3.500   0.7934   0.01598   0.00625  -0.0672   0.4284   1.0000
   3.750   0.8173   0.01629   0.00641  -0.0663   0.4192   1.0000
   4.000   0.8414   0.01657   0.00664  -0.0656   0.4092   1.0000
   4.250   0.8653   0.01688   0.00686  -0.0647   0.4007   1.0000
   4.500   0.8892   0.01718   0.00715  -0.0640   0.3916   1.0000
   4.750   0.9130   0.01751   0.00743  -0.0632   0.3832   1.0000
   5.000   0.9367   0.01783   0.00774  -0.0624   0.3742   1.0000
   5.250   0.9600   0.01815   0.00807  -0.0616   0.3647   1.0000
   5.500   0.9828   0.01849   0.00834  -0.0606   0.3548   1.0000
   5.750   1.0055   0.01880   0.00869  -0.0597   0.3433   1.0000
   6.000   1.0279   0.01913   0.00905  -0.0588   0.3322   1.0000
   6.250   1.0499   0.01948   0.00937  -0.0578   0.3222   1.0000
   6.500   1.0723   0.01985   0.00979  -0.0569   0.3120   1.0000
   6.750   1.0944   0.02024   0.01021  -0.0559   0.3029   1.0000
   7.000   1.1161   0.02064   0.01065  -0.0549   0.2943   1.0000
   7.250   1.1383   0.02107   0.01116  -0.0540   0.2864   1.0000
   7.500   1.1597   0.02152   0.01164  -0.0530   0.2792   1.0000
   7.750   1.1811   0.02198   0.01220  -0.0521   0.2712   1.0000
   8.000   1.2017   0.02245   0.01273  -0.0510   0.2638   1.0000
   8.250   1.2226   0.02295   0.01334  -0.0500   0.2566   1.0000
   8.500   1.2427   0.02345   0.01391  -0.0489   0.2497   1.0000
   8.750   1.2626   0.02397   0.01455  -0.0477   0.2427   1.0000
   9.000   1.2817   0.02451   0.01521  -0.0465   0.2358   1.0000
   9.250   1.3006   0.02507   0.01589  -0.0453   0.2297   1.0000
   9.500   1.3195   0.02566   0.01665  -0.0441   0.2238   1.0000
   9.750   1.3361   0.02626   0.01732  -0.0426   0.2168   1.0000
  10.000   1.3521   0.02688   0.01814  -0.0410   0.2075   1.0000
  10.250   1.3659   0.02755   0.01893  -0.0392   0.1969   1.0000
  10.500   1.3769   0.02832   0.01978  -0.0371   0.1839   1.0000
  10.750   1.3842   0.02921   0.02073  -0.0346   0.1675   1.0000
  11.000   1.3887   0.03028   0.02184  -0.0318   0.1492   1.0000
  11.250   1.3910   0.03160   0.02316  -0.0291   0.1198   1.0000
  11.500   1.3790   0.03394   0.02520  -0.0257   0.0872   1.0000
  11.750   1.3686   0.03654   0.02773  -0.0231   0.0773   1.0000
  12.000   1.3588   0.03937   0.03059  -0.0213   0.0717   1.0000
  12.250   1.3501   0.04238   0.03372  -0.0201   0.0680   1.0000
  12.500   1.3376   0.04607   0.03753  -0.0195   0.0648   1.0000
  12.750   1.3229   0.05041   0.04200  -0.0197   0.0626   1.0000
  13.000   1.3091   0.05504   0.04678  -0.0206   0.0605   1.0000
  13.250   1.2961   0.05996   0.05189  -0.0219   0.0583   1.0000
  13.500   1.2812   0.06543   0.05755  -0.0237   0.0566   1.0000
  13.750   1.2646   0.07138   0.06366  -0.0259   0.0551   1.0000
  14.000   1.2480   0.07745   0.06986  -0.0281   0.0536   1.0000
  14.250   1.2319   0.08353   0.07605  -0.0304   0.0523   1.0000
  14.500   1.2161   0.08956   0.08211  -0.0326   0.0505   1.0000
  14.750   1.2084   0.09458   0.08733  -0.0345   0.0482   1.0000
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