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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 500,000
Max Cl/Cd: 108.14 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe758-il-500000.txt
Download as CSV file: xf-goe758-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1342   0.08388   0.08171  -0.0679   0.9506   0.0330
 -10.000  -0.1436   0.07409   0.07189  -0.0774   0.9422   0.0356
  -9.750  -0.1458   0.06507   0.06285  -0.0843   0.9302   0.0361
  -9.500  -0.1214   0.06241   0.06009  -0.0869   0.9119   0.0367
  -9.250  -0.1096   0.05951   0.05710  -0.0887   0.8920   0.0371
  -9.000  -0.1063   0.05642   0.05393  -0.0897   0.8737   0.0376
  -8.750  -0.1054   0.05338   0.05084  -0.0904   0.8564   0.0385
  -8.500  -0.1125   0.04918   0.04659  -0.0920   0.8401   0.0392
  -8.250  -0.1305   0.04345   0.04082  -0.0952   0.8245   0.0401
  -8.000  -0.1812   0.03449   0.03171  -0.1022   0.8088   0.0394
  -7.750  -0.2222   0.02816   0.02463  -0.1031   0.7917   0.0425
  -7.500  -0.2257   0.02218   0.01850  -0.1030   0.7765   0.0437
  -7.250  -0.2087   0.02083   0.01710  -0.1024   0.7573   0.0444
  -7.000  -0.1932   0.01941   0.01554  -0.1018   0.7383   0.0453
  -6.750  -0.1779   0.01784   0.01377  -0.1011   0.7209   0.0469
  -6.500  -0.1715   0.01477   0.01011  -0.0998   0.7067   0.0519
  -6.250  -0.1506   0.01369   0.00899  -0.0995   0.6946   0.0529
  -6.000  -0.1299   0.01279   0.00797  -0.0990   0.6843   0.0547
  -5.750  -0.1132   0.01138   0.00611  -0.0980   0.6756   0.0614
  -5.500  -0.0902   0.01055   0.00530  -0.0979   0.6681   0.0630
  -5.250  -0.0680   0.01831   0.01176  -0.0999   0.6723   0.0416
  -5.000  -0.0443   0.01671   0.00994  -0.0992   0.6651   0.0400
  -4.750  -0.0192   0.01565   0.00869  -0.0985   0.6584   0.0389
  -4.500   0.0062   0.01491   0.00777  -0.0979   0.6523   0.0385
  -4.250   0.0322   0.01434   0.00714  -0.0975   0.6467   0.0388
  -4.000   0.0581   0.01381   0.00654  -0.0971   0.6411   0.0392
  -3.750   0.0839   0.01335   0.00598  -0.0966   0.6361   0.0392
  -3.500   0.1099   0.01291   0.00550  -0.0961   0.6313   0.0393
  -3.250   0.1358   0.01253   0.00508  -0.0957   0.6263   0.0397
  -3.000   0.1617   0.01223   0.00471  -0.0952   0.6214   0.0400
  -2.750   0.1877   0.01196   0.00439  -0.0948   0.6168   0.0403
  -2.500   0.2139   0.01168   0.00410  -0.0944   0.6119   0.0408
  -2.250   0.2402   0.01147   0.00384  -0.0940   0.6072   0.0415
  -2.000   0.2668   0.01136   0.00365  -0.0937   0.6027   0.0423
  -1.750   0.2932   0.01111   0.00340  -0.0934   0.5986   0.0433
  -1.500   0.3198   0.01090   0.00317  -0.0931   0.5941   0.0446
  -1.250   0.3466   0.01077   0.00300  -0.0928   0.5899   0.0464
  -1.000   0.3739   0.01075   0.00290  -0.0926   0.5857   0.0486
  -0.750   0.4009   0.01063   0.00281  -0.0923   0.5817   0.0526
  -0.500   0.4267   0.01031   0.00273  -0.0920   0.5773   0.1174
  -0.250   0.4499   0.00967   0.00268  -0.0914   0.5731   0.3129
   0.000   0.4731   0.00924   0.00275  -0.0908   0.5691   0.4832
   0.250   0.4971   0.00897   0.00282  -0.0900   0.5650   0.5909
   0.500   0.5219   0.00882   0.00285  -0.0892   0.5604   0.6531
   0.750   0.5458   0.00866   0.00287  -0.0883   0.5561   0.7178
   1.000   0.5672   0.00835   0.00294  -0.0867   0.5519   0.8386
   1.250   0.6618   0.00823   0.00300  -0.1009   0.5452   0.9977
   1.500   0.6910   0.00830   0.00300  -0.1012   0.5403   1.0000
   1.750   0.7156   0.00840   0.00303  -0.1005   0.5356   1.0000
   2.000   0.7403   0.00845   0.00306  -0.0999   0.5303   1.0000
   2.250   0.7651   0.00852   0.00309  -0.0992   0.5252   1.0000
   2.500   0.7897   0.00863   0.00314  -0.0986   0.5202   1.0000
   2.750   0.8146   0.00868   0.00319  -0.0979   0.5142   1.0000
   3.000   0.8391   0.00877   0.00324  -0.0973   0.5084   1.0000
   3.250   0.8638   0.00887   0.00331  -0.0966   0.5027   1.0000
   3.500   0.8885   0.00895   0.00338  -0.0960   0.4961   1.0000
   4.000   0.9374   0.00916   0.00356  -0.0947   0.4828   1.0000
   4.250   0.9614   0.00930   0.00364  -0.0939   0.4760   1.0000
   4.500   0.9860   0.00941   0.00377  -0.0933   0.4689   1.0000
   4.750   1.0098   0.00956   0.00388  -0.0925   0.4613   1.0000
   5.000   1.0340   0.00970   0.00402  -0.0919   0.4536   1.0000
   5.250   1.0571   0.00988   0.00415  -0.0910   0.4448   1.0000
   5.500   1.0808   0.01003   0.00430  -0.0903   0.4353   1.0000
   5.750   1.1034   0.01023   0.00446  -0.0893   0.4259   1.0000
   6.000   1.1266   0.01042   0.00464  -0.0885   0.4170   1.0000
   6.250   1.1495   0.01063   0.00484  -0.0877   0.4091   1.0000
   6.500   1.1722   0.01085   0.00505  -0.0868   0.4011   1.0000
   6.750   1.1946   0.01108   0.00528  -0.0859   0.3935   1.0000
   7.000   1.2162   0.01133   0.00551  -0.0849   0.3846   1.0000
   7.250   1.2380   0.01156   0.00575  -0.0839   0.3756   1.0000
   7.500   1.2578   0.01188   0.00602  -0.0826   0.3663   1.0000
   7.750   1.2793   0.01211   0.00628  -0.0816   0.3575   1.0000
   8.000   1.2989   0.01242   0.00658  -0.0802   0.3494   1.0000
   8.250   1.3182   0.01271   0.00687  -0.0789   0.3397   1.0000
   8.500   1.3369   0.01302   0.00718  -0.0774   0.3299   1.0000
   8.750   1.3525   0.01339   0.00752  -0.0754   0.3216   1.0000
   9.000   1.3702   0.01366   0.00784  -0.0737   0.3137   1.0000
   9.250   1.3835   0.01407   0.00823  -0.0713   0.3053   1.0000
   9.500   1.3999   0.01440   0.00859  -0.0695   0.2959   1.0000
   9.750   1.4141   0.01483   0.00902  -0.0674   0.2866   1.0000
  10.000   1.4258   0.01536   0.00954  -0.0651   0.2747   1.0000
  10.250   1.4379   0.01592   0.01008  -0.0629   0.2621   1.0000
  10.500   1.4469   0.01664   0.01076  -0.0604   0.2449   1.0000
  10.750   1.4510   0.01765   0.01167  -0.0574   0.2206   1.0000
  11.000   1.4497   0.01904   0.01292  -0.0541   0.1922   1.0000
  11.250   1.4387   0.02115   0.01479  -0.0501   0.1532   1.0000
  11.500   1.4175   0.02419   0.01755  -0.0459   0.1075   1.0000
  11.750   1.4044   0.02702   0.02025  -0.0430   0.0838   1.0000
  12.000   1.3961   0.02971   0.02289  -0.0409   0.0664   1.0000
  12.250   1.3845   0.03290   0.02596  -0.0391   0.0435   1.0000
  12.500   1.3732   0.03631   0.02931  -0.0378   0.0313   1.0000
  12.750   1.3683   0.03929   0.03232  -0.0369   0.0274   1.0000
  13.000   1.3685   0.04183   0.03495  -0.0363   0.0256   1.0000
  13.250   1.3669   0.04465   0.03784  -0.0358   0.0241   1.0000
  13.500   1.3641   0.04764   0.04090  -0.0354   0.0232   1.0000
  13.750   1.3583   0.05103   0.04438  -0.0350   0.0223   1.0000
  14.000   1.3570   0.05401   0.04746  -0.0348   0.0216   1.0000
  14.250   1.3549   0.05710   0.05064  -0.0347   0.0211   1.0000
  14.500   1.3512   0.06046   0.05408  -0.0347   0.0205   1.0000
  14.750   1.3459   0.06409   0.05781  -0.0348   0.0200   1.0000
  15.000   1.3403   0.06784   0.06164  -0.0351   0.0196   1.0000
  15.250   1.3307   0.07219   0.06608  -0.0355   0.0190   1.0000
  15.500   1.3215   0.07662   0.07059  -0.0361   0.0187   1.0000
  15.750   1.3114   0.08121   0.07527  -0.0367   0.0184   1.0000
  16.000   1.3086   0.08489   0.07904  -0.0373   0.0183   1.0000
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