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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.93 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe323-il-1000000.txt
Download as CSV file: xf-goe323-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3831   0.11678   0.11391   0.0097   0.6238   0.0189
  -9.750  -0.3764   0.11366   0.11078   0.0083   0.6206   0.0195
  -8.750  -0.3680   0.09649   0.09360  -0.0030   0.6087   0.0209
  -8.500  -0.3584   0.09388   0.09096  -0.0033   0.6049   0.0211
  -7.750  -0.2375   0.07563   0.07280  -0.0135   0.5868   0.0225
  -7.500  -0.2341   0.07213   0.06931  -0.0150   0.5845   0.0231
  -7.000  -0.3023   0.07611   0.07318  -0.0174   0.5866   0.0228
  -6.750  -0.2801   0.06777   0.06475  -0.0320   0.5847   0.0243
  -6.500  -0.2602   0.06250   0.05940  -0.0377   0.5821   0.0244
  -6.250  -0.2470   0.05723   0.05407  -0.0411   0.5795   0.0246
  -6.000  -0.2284   0.05498   0.05176  -0.0423   0.5764   0.0248
  -5.750  -0.2081   0.05277   0.04949  -0.0437   0.5729   0.0250
  -5.500  -0.1862   0.05028   0.04695  -0.0454   0.5704   0.0253
  -5.250  -0.1629   0.04759   0.04420  -0.0473   0.5679   0.0257
  -5.000  -0.1385   0.04471   0.04122  -0.0493   0.5654   0.0264
  -4.750  -0.1025   0.03803   0.03417  -0.0532   0.5632   0.0284
  -4.500  -0.0822   0.03281   0.02872  -0.0547   0.5610   0.0288
  -4.250  -0.0582   0.03148   0.02732  -0.0551   0.5581   0.0291
  -4.000  -0.0333   0.03020   0.02596  -0.0554   0.5548   0.0294
  -3.750  -0.0075   0.02866   0.02434  -0.0557   0.5518   0.0298
  -3.500   0.0189   0.02695   0.02252  -0.0560   0.5485   0.0305
  -3.250   0.0503   0.02406   0.01910  -0.0555   0.5455   0.0330
  -3.000   0.0737   0.02034   0.01511  -0.0558   0.5424   0.0337
  -2.750   0.1004   0.01940   0.01410  -0.0558   0.5384   0.0340
  -2.500   0.1278   0.01851   0.01315  -0.0558   0.5356   0.0344
  -2.250   0.1554   0.01769   0.01225  -0.0558   0.5326   0.0350
  -2.000   0.1839   0.01464   0.00864  -0.0550   0.5301   0.0325
  -1.750   0.2116   0.01332   0.00714  -0.0548   0.5272   0.0320
  -1.500   0.2397   0.01242   0.00607  -0.0546   0.5240   0.0319
  -1.250   0.2680   0.01169   0.00523  -0.0544   0.5213   0.0319
  -1.000   0.2965   0.01112   0.00460  -0.0543   0.5187   0.0321
  -0.750   0.3251   0.01080   0.00422  -0.0542   0.5157   0.0327
  -0.500   0.3536   0.01051   0.00388  -0.0541   0.5125   0.0332
  -0.250   0.3813   0.00989   0.00323  -0.0539   0.5092   0.0338
   0.000   0.4094   0.00967   0.00300  -0.0538   0.5056   0.0345
   0.250   0.4380   0.00946   0.00282  -0.0538   0.5026   0.0351
   0.500   0.4666   0.00927   0.00264  -0.0537   0.4988   0.0358
   0.750   0.4950   0.00912   0.00248  -0.0537   0.4943   0.0366
   1.000   0.5234   0.00902   0.00235  -0.0536   0.4896   0.0375
   1.250   0.5522   0.00892   0.00227  -0.0536   0.4859   0.0383
   1.500   0.5806   0.00870   0.00207  -0.0536   0.4814   0.0403
   1.750   0.6091   0.00865   0.00200  -0.0536   0.4764   0.0419
   2.000   0.6378   0.00860   0.00196  -0.0536   0.4717   0.0437
   2.250   0.6665   0.00850   0.00187  -0.0536   0.4665   0.0460
   2.500   0.6950   0.00847   0.00183  -0.0537   0.4608   0.0495
   2.750   0.7236   0.00843   0.00181  -0.0537   0.4551   0.0548
   3.000   0.7522   0.00839   0.00179  -0.0537   0.4477   0.0668
   3.250   0.7837   0.00645   0.00200  -0.0551   0.4395   1.0000
   3.500   0.8114   0.00657   0.00203  -0.0550   0.4274   1.0000
   3.750   0.8390   0.00671   0.00209  -0.0549   0.4117   1.0000
   4.000   0.8664   0.00688   0.00217  -0.0548   0.3932   1.0000
   4.250   0.8935   0.00711   0.00229  -0.0547   0.3739   1.0000
   4.500   0.9204   0.00736   0.00244  -0.0545   0.3555   1.0000
   4.750   0.9472   0.00763   0.00261  -0.0544   0.3391   1.0000
   5.000   0.9741   0.00788   0.00279  -0.0543   0.3253   1.0000
   5.250   1.0011   0.00812   0.00296  -0.0542   0.3138   1.0000
   5.750   1.0552   0.00856   0.00332  -0.0541   0.2953   1.0000
   6.000   1.0820   0.00881   0.00352  -0.0540   0.2860   1.0000
   6.250   1.1090   0.00903   0.00370  -0.0540   0.2771   1.0000
   6.500   1.1358   0.00926   0.00391  -0.0539   0.2691   1.0000
   6.750   1.1627   0.00949   0.00410  -0.0539   0.2614   1.0000
   7.000   1.1893   0.00973   0.00432  -0.0538   0.2543   1.0000
   7.250   1.2160   0.00996   0.00453  -0.0538   0.2473   1.0000
   7.500   1.2423   0.01024   0.00478  -0.0537   0.2400   1.0000
   7.750   1.2687   0.01048   0.00501  -0.0537   0.2324   1.0000
   8.000   1.2945   0.01079   0.00528  -0.0536   0.2240   1.0000
   8.250   1.3204   0.01107   0.00554  -0.0535   0.2163   1.0000
   8.500   1.3460   0.01138   0.00583  -0.0534   0.2092   1.0000
   8.750   1.3716   0.01168   0.00611  -0.0532   0.2020   1.0000
   9.000   1.3967   0.01203   0.00644  -0.0531   0.1946   1.0000
   9.250   1.4218   0.01234   0.00674  -0.0529   0.1881   1.0000
   9.500   1.4463   0.01272   0.00710  -0.0527   0.1814   1.0000
   9.750   1.4711   0.01304   0.00743  -0.0526   0.1753   1.0000
  10.000   1.4946   0.01349   0.00784  -0.0523   0.1679   1.0000
  10.250   1.5189   0.01384   0.00820  -0.0521   0.1616   1.0000
  10.500   1.5414   0.01434   0.00867  -0.0517   0.1534   1.0000
  10.750   1.5640   0.01480   0.00911  -0.0513   0.1452   1.0000
  11.000   1.5853   0.01535   0.00963  -0.0509   0.1351   1.0000
  11.250   1.6034   0.01615   0.01034  -0.0501   0.1192   1.0000
  11.500   1.6167   0.01730   0.01134  -0.0489   0.0988   1.0000
  11.750   1.6294   0.01840   0.01237  -0.0477   0.0871   1.0000
  12.000   1.6417   0.01940   0.01336  -0.0464   0.0794   1.0000
  12.250   1.6474   0.02069   0.01464  -0.0445   0.0723   1.0000
  12.500   1.6520   0.02237   0.01631  -0.0435   0.0634   1.0000
  12.750   1.6399   0.02623   0.02002  -0.0434   0.0393   1.0000
  13.000   1.6234   0.03092   0.02467  -0.0437   0.0225   1.0000
  13.250   1.6215   0.03388   0.02768  -0.0436   0.0193   1.0000
  13.500   1.6199   0.03675   0.03060  -0.0435   0.0177   1.0000
  13.750   1.6204   0.03938   0.03330  -0.0433   0.0168   1.0000
  14.000   1.6199   0.04209   0.03609  -0.0432   0.0161   1.0000
  14.250   1.6174   0.04502   0.03910  -0.0430   0.0156   1.0000
  14.500   1.6126   0.04822   0.04237  -0.0429   0.0150   1.0000
  14.750   1.6061   0.05166   0.04589  -0.0428   0.0145   1.0000
  15.000   1.6010   0.05499   0.04931  -0.0428   0.0142   1.0000
  15.250   1.5990   0.05814   0.05254  -0.0430   0.0139   1.0000
  15.500   1.5956   0.06157   0.05606  -0.0434   0.0137   1.0000
  15.750   1.5909   0.06520   0.05978  -0.0438   0.0134   1.0000
  16.000   1.5857   0.06899   0.06366  -0.0443   0.0131   1.0000
  16.250   1.5795   0.07296   0.06771  -0.0450   0.0129   1.0000
  16.500   1.5717   0.07719   0.07203  -0.0457   0.0127   1.0000
  16.750   1.5624   0.08176   0.07670  -0.0466   0.0125   1.0000
  17.000   1.5513   0.08666   0.08170  -0.0477   0.0123   1.0000
  17.250   1.5382   0.09191   0.08705  -0.0490   0.0121   1.0000
  17.500   1.5236   0.09753   0.09278  -0.0505   0.0120   1.0000
  17.750   1.5072   0.10356   0.09892  -0.0523   0.0118   1.0000
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