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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 100,000
Max Cl/Cd: 51.99 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe316-il-100000-n5.txt
Download as CSV file: xf-goe316-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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  -0.3729   0.09919   0.09456  -0.0096   1.0000   0.0445
  -8.000  -0.3686   0.09603   0.09146  -0.0121   1.0000   0.0459
  -7.750  -0.3669   0.09312   0.08862  -0.0162   1.0000   0.0472
  -7.500  -0.3597   0.08969   0.08522  -0.0245   1.0000   0.0479
  -7.250  -0.3475   0.08594   0.08141  -0.0330   1.0000   0.0482
  -7.000  -0.3405   0.08113   0.07671  -0.0311   1.0000   0.0490
  -6.750  -0.3318   0.07788   0.07353  -0.0286   1.0000   0.0505
  -6.500  -0.3211   0.07463   0.07031  -0.0301   1.0000   0.0520
  -6.250  -0.3105   0.07139   0.06709  -0.0323   1.0000   0.0536
  -6.000  -0.2885   0.06743   0.06306  -0.0381   0.9878   0.0565
  -5.750  -0.2449   0.06193   0.05713  -0.0505   0.9639   0.0598
  -5.500  -0.2252   0.05800   0.05331  -0.0509   0.9454   0.0622
  -5.250  -0.1976   0.05459   0.04976  -0.0541   0.9232   0.0659
  -5.000  -0.1576   0.05160   0.04607  -0.0606   0.9017   0.0721
  -4.750  -0.1398   0.04749   0.04204  -0.0608   0.8818   0.0738
  -4.500  -0.1191   0.04500   0.03947  -0.0609   0.8627   0.0781
  -4.250  -0.0916   0.04252   0.03655  -0.0626   0.8453   0.0878
  -4.000  -0.0706   0.04006   0.03400  -0.0624   0.8284   0.0913
  -3.750  -0.0430   0.03826   0.03170  -0.0631   0.8121   0.1019
  -3.500  -0.0115   0.03452   0.02748  -0.0629   0.7975   0.0689
  -3.250   0.0134   0.03251   0.02518  -0.0630   0.7828   0.0748
  -3.000   0.0461   0.03012   0.02207  -0.0624   0.7702   0.0583
  -2.750   0.0721   0.02816   0.01990  -0.0623   0.7575   0.0570
  -2.500   0.0992   0.02655   0.01799  -0.0621   0.7450   0.0560
  -2.250   0.1266   0.02516   0.01626  -0.0617   0.7324   0.0553
  -2.000   0.1547   0.02405   0.01483  -0.0614   0.7190   0.0563
  -1.750   0.1828   0.02315   0.01362  -0.0611   0.7057   0.0578
  -1.500   0.2106   0.02215   0.01237  -0.0607   0.6924   0.0577
  -1.250   0.2383   0.02124   0.01124  -0.0604   0.6785   0.0575
  -1.000   0.2659   0.02044   0.01025  -0.0600   0.6638   0.0576
  -0.750   0.2935   0.01972   0.00937  -0.0596   0.6482   0.0579
  -0.500   0.3208   0.01911   0.00860  -0.0591   0.6316   0.0584
  -0.250   0.3480   0.01857   0.00794  -0.0587   0.6142   0.0595
   0.000   0.3743   0.01793   0.00730  -0.0583   0.5963   0.0625
   0.250   0.4007   0.01753   0.00683  -0.0579   0.5786   0.0650
   0.500   0.4271   0.01717   0.00639  -0.0573   0.5604   0.0663
   0.750   0.4535   0.01691   0.00602  -0.0569   0.5423   0.0679
   1.000   0.4801   0.01677   0.00572  -0.0564   0.5245   0.0700
   1.250   0.5068   0.01668   0.00547  -0.0561   0.5073   0.0726
   1.500   0.5339   0.01664   0.00531  -0.0559   0.4906   0.0786
   1.750   0.5611   0.01667   0.00523  -0.0557   0.4751   0.0892
   2.000   0.5886   0.01667   0.00518  -0.0555   0.4612   0.1080
   2.250   0.6156   0.01474   0.00518  -0.0553   0.4495   1.0000
   2.750   0.6694   0.01529   0.00535  -0.0548   0.4304   1.0000
   3.000   0.6961   0.01559   0.00549  -0.0546   0.4232   1.0000
   3.250   0.7231   0.01588   0.00571  -0.0545   0.4160   1.0000
   3.500   0.7498   0.01621   0.00591  -0.0543   0.4104   1.0000
   3.750   0.7767   0.01652   0.00620  -0.0542   0.4046   1.0000
   4.000   0.8035   0.01685   0.00647  -0.0541   0.3992   1.0000
   4.250   0.8301   0.01721   0.00674  -0.0540   0.3948   1.0000
   4.500   0.8570   0.01756   0.00713  -0.0539   0.3903   1.0000
   4.750   0.8838   0.01793   0.00751  -0.0538   0.3864   1.0000
   5.000   0.9106   0.01832   0.00789  -0.0537   0.3829   1.0000
   5.250   0.9372   0.01873   0.00828  -0.0536   0.3800   1.0000
   5.500   0.9639   0.01916   0.00879  -0.0536   0.3768   1.0000
   5.750   0.9904   0.01959   0.00931  -0.0535   0.3731   1.0000
   6.000   1.0168   0.02004   0.00982  -0.0534   0.3696   1.0000
   6.250   1.0433   0.02050   0.01034  -0.0533   0.3664   1.0000
   6.500   1.0693   0.02098   0.01087  -0.0532   0.3624   1.0000
   6.750   1.0944   0.02139   0.01143  -0.0530   0.3554   1.0000
   7.000   1.1198   0.02179   0.01179  -0.0527   0.3484   1.0000
   7.250   1.1440   0.02220   0.01242  -0.0523   0.3406   1.0000
   7.500   1.1691   0.02262   0.01287  -0.0520   0.3344   1.0000
   7.750   1.1933   0.02310   0.01353  -0.0517   0.3281   1.0000
   8.000   1.2174   0.02352   0.01411  -0.0513   0.3210   1.0000
   8.250   1.2413   0.02397   0.01467  -0.0509   0.3142   1.0000
   8.500   1.2644   0.02443   0.01536  -0.0504   0.3069   1.0000
   8.750   1.2879   0.02485   0.01587  -0.0500   0.3001   1.0000
   9.000   1.3097   0.02532   0.01667  -0.0493   0.2916   1.0000
   9.250   1.3315   0.02571   0.01725  -0.0486   0.2827   1.0000
   9.500   1.3511   0.02601   0.01777  -0.0477   0.2687   1.0000
   9.750   1.3694   0.02634   0.01839  -0.0467   0.2477   1.0000
  10.000   1.3862   0.02678   0.01898  -0.0456   0.2117   1.0000
  10.250   1.3924   0.02806   0.01986  -0.0436   0.1628   1.0000
  10.500   1.3937   0.03015   0.02174  -0.0415   0.1296   1.0000
  10.750   1.3932   0.03233   0.02386  -0.0392   0.1044   1.0000
  11.000   1.3882   0.03456   0.02608  -0.0366   0.0854   1.0000
  11.250   1.3797   0.03732   0.02883  -0.0346   0.0738   1.0000
  11.500   1.3697   0.04063   0.03219  -0.0337   0.0667   1.0000
  11.750   1.3580   0.04456   0.03621  -0.0336   0.0616   1.0000
  12.250   1.3322   0.05380   0.04574  -0.0352   0.0545   1.0000
  12.500   1.3181   0.05901   0.05111  -0.0366   0.0517   1.0000
  12.750   1.3021   0.06468   0.05691  -0.0384   0.0496   1.0000
  13.000   1.2854   0.07058   0.06292  -0.0402   0.0478   1.0000
  13.250   1.2708   0.07616   0.06859  -0.0418   0.0459   1.0000
  13.500   1.2615   0.08100   0.07359  -0.0430   0.0431   1.0000
  13.750   1.2518   0.08592   0.07863  -0.0443   0.0405   1.0000
  14.000   1.2424   0.09089   0.08369  -0.0458   0.0384   1.0000
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