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GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il)
Reynolds number: 50,000
Max Cl/Cd: 29.32 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe320-il-50000.txt
Download as CSV file: xf-goe320-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3437   0.12667   0.12105  -0.0099   1.0000   0.1333
  -7.250  -0.3670   0.12705   0.12151  -0.0086   1.0000   0.1338
  -7.000  -0.3859   0.12726   0.12178  -0.0102   1.0000   0.1343
  -6.750  -0.3755   0.12193   0.11652  -0.0064   1.0000   0.1359
  -6.500  -0.3697   0.11853   0.11316  -0.0037   1.0000   0.1383
  -6.250  -0.3726   0.11644   0.11111  -0.0024   1.0000   0.1410
  -6.000  -0.3780   0.11463   0.10936  -0.0020   1.0000   0.1439
  -5.750  -0.3851   0.11320   0.10795  -0.0033   1.0000   0.1473
  -5.500  -0.3919   0.11372   0.10838  -0.0125   1.0000   0.1500
  -5.250  -0.3886   0.10855   0.10336  -0.0064   1.0000   0.1519
  -5.000  -0.3856   0.10560   0.10046  -0.0036   1.0000   0.1553
  -4.750  -0.3826   0.10331   0.09819  -0.0040   1.0000   0.1602
  -4.500  -0.3719   0.10223   0.09699  -0.0137   1.0000   0.1665
  -4.250  -0.3708   0.09821   0.09308  -0.0091   1.0000   0.1689
  -4.000  -0.3655   0.09557   0.09049  -0.0077   1.0000   0.1735
  -3.750  -0.3446   0.09419   0.08894  -0.0167   1.0000   0.1835
  -3.500  -0.3430   0.09051   0.08538  -0.0129   1.0000   0.1865
  -3.250  -0.2808   0.08653   0.08129  -0.0249   0.9820   0.2039
  -3.000  -0.2345   0.08307   0.07774  -0.0327   0.9637   0.2222
  -2.750  -0.1971   0.07999   0.07464  -0.0378   0.9488   0.2421
  -2.500  -0.1575   0.07763   0.07218  -0.0443   0.9346   0.2756
  -2.250  -0.1250   0.07467   0.06926  -0.0466   0.9216   0.3139
  -2.000  -0.1088   0.07217   0.06687  -0.0451   0.9085   0.3541
  -1.500  -0.0811   0.06763   0.06259  -0.0379   0.8818   0.4726
  -1.250  -0.0617   0.06520   0.06029  -0.0338   0.8689   0.5344
  -1.000  -0.0496   0.06329   0.05847  -0.0303   0.8533   0.5792
  -0.750  -0.0301   0.06126   0.05650  -0.0282   0.8374   0.6192
  -0.500   0.0009   0.05909   0.05435  -0.0291   0.8208   0.6502
  -0.250   0.0594   0.05710   0.05224  -0.0380   0.8019   0.6640
   0.000   0.1632   0.05479   0.04955  -0.0591   0.7802   0.6207
   0.250   0.3648   0.05471   0.04703  -0.0994   0.7566   0.2862
   0.500   0.4163   0.05403   0.04570  -0.1019   0.7386   0.2328
   0.750   0.4582   0.05310   0.04439  -0.1029   0.7210   0.2136
   1.000   0.4983   0.05249   0.04334  -0.1033   0.7038   0.1991
   1.250   0.5342   0.05146   0.04213  -0.1036   0.6875   0.1914
   1.500   0.6031   0.04877   0.03902  -0.1061   0.6808   0.1872
   1.750   0.6291   0.04846   0.03855  -0.1049   0.6641   0.1901
   2.000   0.6544   0.04839   0.03829  -0.1036   0.6479   0.1921
   2.250   0.6786   0.04843   0.03817  -0.1023   0.6327   0.1965
   2.500   0.7402   0.04498   0.03458  -0.1027   0.6271   0.2144
   2.750   0.7620   0.04464   0.03425  -0.1009   0.6112   0.2308
   3.000   0.7876   0.04392   0.03361  -0.0994   0.5961   0.2620
   3.250   0.8183   0.04117   0.03237  -0.0974   0.5839   1.0000
   3.500   0.8716   0.03880   0.02914  -0.0966   0.5749   1.0000
   3.750   0.8909   0.03927   0.02939  -0.0949   0.5601   1.0000
   4.000   0.9134   0.03958   0.02950  -0.0935   0.5469   1.0000
   4.250   0.9685   0.03713   0.02667  -0.0940   0.5389   1.0000
   4.500   0.9835   0.03810   0.02757  -0.0923   0.5245   1.0000
   4.750   1.0025   0.03878   0.02815  -0.0909   0.5112   1.0000
   5.000   1.0329   0.03854   0.02774  -0.0901   0.4993   1.0000
   5.250   1.0804   0.03701   0.02590  -0.0906   0.4886   1.0000
   5.500   1.0947   0.03823   0.02709  -0.0890   0.4750   1.0000
   5.750   1.1133   0.03930   0.02811  -0.0877   0.4626   1.0000
   6.000   1.1480   0.03928   0.02786  -0.0877   0.4517   1.0000
   6.250   1.1733   0.04002   0.02849  -0.0871   0.4400   1.0000
   6.500   1.1817   0.04211   0.03064  -0.0852   0.4286   1.0000
   6.750   1.2206   0.04220   0.03046  -0.0858   0.4189   1.0000
   7.000   1.2174   0.04513   0.03361  -0.0831   0.4090   1.0000
   7.250   1.2510   0.04585   0.03413  -0.0834   0.4011   1.0000
   7.500   1.2181   0.05108   0.03976  -0.0789   0.3939   1.0000
   7.750   1.2491   0.05201   0.04059  -0.0791   0.3878   1.0000
   8.000   1.2376   0.05621   0.04492  -0.0766   0.3830   1.0000
   8.250   0.7800   0.12232   0.11232  -0.0908   0.4351   1.0000
   8.500   0.8178   0.12248   0.11234  -0.0893   0.4197   1.0000
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