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GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 599 AIRFOIL (goe599-il)
Reynolds number: 100,000
Max Cl/Cd: 44.06 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe599-il-100000-n5.txt
Download as CSV file: xf-goe599-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 599 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5822   0.08815   0.08308  -0.0320   1.0000   0.0254
 -10.000  -0.6428   0.06638   0.06122  -0.0496   1.0000   0.0233
  -9.750  -0.6720   0.06066   0.05531  -0.0523   1.0000   0.0229
  -9.500  -0.6898   0.05658   0.05102  -0.0518   1.0000   0.0229
  -9.250  -0.7017   0.05259   0.04678  -0.0506   1.0000   0.0229
  -9.000  -0.7087   0.04876   0.04267  -0.0490   1.0000   0.0230
  -8.750  -0.7103   0.04522   0.03884  -0.0473   1.0000   0.0233
  -8.500  -0.7068   0.04210   0.03544  -0.0456   1.0000   0.0238
  -8.250  -0.6996   0.03934   0.03238  -0.0439   1.0000   0.0244
  -8.000  -0.6888   0.03714   0.02993  -0.0424   1.0000   0.0255
  -7.750  -0.6759   0.03509   0.02759  -0.0409   1.0000   0.0272
  -7.500  -0.6618   0.03276   0.02485  -0.0393   1.0000   0.0289
  -7.250  -0.6457   0.03043   0.02208  -0.0377   1.0000   0.0302
  -7.000  -0.6273   0.02853   0.01977  -0.0362   1.0000   0.0315
  -6.750  -0.6097   0.02660   0.01774  -0.0350   1.0000   0.0340
  -6.500  -0.5903   0.02536   0.01639  -0.0339   1.0000   0.0372
  -6.250  -0.5700   0.02400   0.01482  -0.0326   1.0000   0.0400
  -6.000  -0.5499   0.02268   0.01338  -0.0315   1.0000   0.0437
  -5.750  -0.5299   0.02165   0.01233  -0.0304   1.0000   0.0486
  -5.500  -0.5089   0.02075   0.01127  -0.0293   1.0000   0.0535
  -5.250  -0.4882   0.01988   0.01042  -0.0285   1.0000   0.0607
  -5.000  -0.4665   0.01919   0.00963  -0.0276   1.0000   0.0683
  -4.750  -0.4444   0.01863   0.00910  -0.0268   1.0000   0.0809
  -4.500  -0.4219   0.01801   0.00848  -0.0261   1.0000   0.0989
  -4.250  -0.3991   0.01736   0.00785  -0.0256   1.0000   0.1243
  -4.000  -0.3761   0.01668   0.00742  -0.0253   1.0000   0.1676
  -3.750  -0.3527   0.01620   0.00718  -0.0251   1.0000   0.2325
  -3.500  -0.3212   0.01578   0.00695  -0.0264   0.9971   0.2978
  -3.250  -0.2871   0.01530   0.00681  -0.0283   0.9930   0.3816
  -3.000  -0.2538   0.01491   0.00674  -0.0298   0.9883   0.4668
  -2.750  -0.2195   0.01471   0.00667  -0.0313   0.9836   0.5269
  -2.500  -0.1860   0.01455   0.00659  -0.0326   0.9780   0.5796
  -2.250  -0.1527   0.01441   0.00652  -0.0337   0.9727   0.6270
  -2.000  -0.1204   0.01427   0.00648  -0.0346   0.9668   0.6742
  -1.750  -0.0876   0.01415   0.00646  -0.0354   0.9614   0.7230
  -1.500  -0.0577   0.01404   0.00647  -0.0354   0.9546   0.7751
  -1.250  -0.0225   0.01397   0.00650  -0.0364   0.9503   0.8318
  -1.000   0.0105   0.01394   0.00653  -0.0370   0.9429   0.8887
  -0.750   0.0586   0.01394   0.00651  -0.0410   0.9389   0.9426
  -0.500   0.1138   0.01389   0.00640  -0.0467   0.9357   0.9838
  -0.250   0.1545   0.01378   0.00623  -0.0496   0.9252   1.0000
   0.000   0.1884   0.01364   0.00603  -0.0509   0.9133   1.0000
   0.250   0.2224   0.01350   0.00585  -0.0521   0.9022   1.0000
   0.500   0.2569   0.01337   0.00569  -0.0534   0.8924   1.0000
   0.750   0.2863   0.01332   0.00561  -0.0537   0.8806   1.0000
   1.000   0.3164   0.01327   0.00556  -0.0541   0.8694   1.0000
   1.250   0.3475   0.01322   0.00551  -0.0547   0.8587   1.0000
   1.500   0.3792   0.01316   0.00547  -0.0553   0.8475   1.0000
   1.750   0.4098   0.01306   0.00537  -0.0554   0.8304   1.0000
   2.000   0.4413   0.01292   0.00521  -0.0555   0.8084   1.0000
   2.250   0.4688   0.01289   0.00513  -0.0548   0.7810   1.0000
   2.500   0.4947   0.01291   0.00512  -0.0540   0.7521   1.0000
   2.750   0.5197   0.01296   0.00515  -0.0529   0.7195   1.0000
   3.000   0.5439   0.01306   0.00519  -0.0518   0.6813   1.0000
   3.250   0.5684   0.01321   0.00524  -0.0507   0.6387   1.0000
   3.500   0.5921   0.01345   0.00533  -0.0494   0.5866   1.0000
   3.750   0.6129   0.01391   0.00544  -0.0477   0.5107   1.0000
   4.000   0.6311   0.01463   0.00569  -0.0458   0.4212   1.0000
   4.250   0.6486   0.01552   0.00609  -0.0440   0.3259   1.0000
   4.500   0.6611   0.01716   0.00676  -0.0419   0.1562   1.0000
   4.750   0.6817   0.01805   0.00746  -0.0408   0.1158   1.0000
   5.000   0.7037   0.01874   0.00810  -0.0398   0.1008   1.0000
   5.250   0.7254   0.01943   0.00878  -0.0388   0.0934   1.0000
   5.500   0.7472   0.02007   0.00953  -0.0378   0.0891   1.0000
   5.750   0.7685   0.02075   0.01030  -0.0368   0.0849   1.0000
   6.000   0.7882   0.02159   0.01115  -0.0355   0.0807   1.0000
   6.250   0.8086   0.02239   0.01204  -0.0343   0.0776   1.0000
   6.500   0.8291   0.02325   0.01301  -0.0331   0.0753   1.0000
   6.750   0.8500   0.02421   0.01409  -0.0320   0.0728   1.0000
   7.000   0.8712   0.02530   0.01520  -0.0310   0.0698   1.0000
   7.250   0.8926   0.02661   0.01654  -0.0302   0.0651   1.0000
   7.500   0.9142   0.02756   0.01768  -0.0294   0.0593   1.0000
   7.750   0.9349   0.02910   0.01917  -0.0287   0.0538   1.0000
   8.000   0.9562   0.03034   0.02073  -0.0277   0.0485   1.0000
   8.250   0.9757   0.03157   0.02214  -0.0267   0.0433   1.0000
   8.500   0.9947   0.03324   0.02399  -0.0256   0.0387   1.0000
   8.750   1.0135   0.03496   0.02601  -0.0243   0.0347   1.0000
   9.000   1.0297   0.03606   0.02713  -0.0232   0.0322   1.0000
   9.250   1.0452   0.03845   0.03004  -0.0214   0.0288   1.0000
   9.500   1.0586   0.04065   0.03256  -0.0197   0.0268   1.0000
   9.750   1.0705   0.04244   0.03455  -0.0180   0.0255   1.0000
  10.000   1.0810   0.04394   0.03613  -0.0164   0.0245   1.0000
  10.250   1.0798   0.04809   0.04090  -0.0132   0.0233   1.0000
  10.500   1.0732   0.05189   0.04519  -0.0100   0.0223   1.0000
  10.750   1.0616   0.05528   0.04893  -0.0065   0.0217   1.0000
  11.000   1.0470   0.05880   0.05276  -0.0035   0.0212   1.0000
  11.250   1.0292   0.06277   0.05700  -0.0015   0.0210   1.0000
  11.500   1.0083   0.06741   0.06190  -0.0007   0.0209   1.0000
  11.750   0.9844   0.07298   0.06772  -0.0016   0.0210   1.0000
  12.000   0.9574   0.07990   0.07484  -0.0046   0.0213   1.0000
  12.250   0.9283   0.08858   0.08370  -0.0099   0.0218   1.0000
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