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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.17 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe457-il-1000000-n5.txt
Download as CSV file: xf-goe457-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3871   0.11237   0.11069  -0.0210   1.0000   0.0046
  -9.500  -0.5540   0.02021   0.01707  -0.0995   0.9775   0.0060
  -9.250  -0.5307   0.01767   0.01421  -0.1003   0.9743   0.0064
  -9.000  -0.5061   0.01621   0.01255  -0.1005   0.9707   0.0067
  -8.750  -0.4779   0.01507   0.01124  -0.1012   0.9684   0.0071
  -8.500  -0.4482   0.01411   0.01013  -0.1021   0.9667   0.0075
  -8.250  -0.4178   0.01329   0.00915  -0.1030   0.9654   0.0080
  -8.000  -0.3929   0.01264   0.00837  -0.1025   0.9605   0.0084
  -7.750  -0.3640   0.01197   0.00761  -0.1029   0.9571   0.0094
  -7.500  -0.3329   0.01141   0.00697  -0.1037   0.9542   0.0102
  -7.250  -0.3032   0.01093   0.00640  -0.1042   0.9500   0.0111
  -7.000  -0.2738   0.01051   0.00590  -0.1045   0.9442   0.0121
  -6.750  -0.2418   0.01033   0.00571  -0.1053   0.9397   0.0134
  -6.500  -0.2125   0.01014   0.00549  -0.1055   0.9341   0.0147
  -6.250  -0.1831   0.00990   0.00518  -0.1057   0.9276   0.0157
  -6.000  -0.1529   0.00993   0.00523  -0.1060   0.9206   0.0168
  -5.750  -0.1241   0.00994   0.00523  -0.1061   0.9130   0.0176
  -5.500  -0.0958   0.00984   0.00507  -0.1060   0.9052   0.0186
  -5.250  -0.0683   0.00972   0.00488  -0.1057   0.8971   0.0196
  -5.000  -0.0407   0.00966   0.00477  -0.1055   0.8890   0.0204
  -4.750  -0.0134   0.00958   0.00463  -0.1052   0.8807   0.0209
  -4.500   0.0138   0.00956   0.00456  -0.1049   0.8716   0.0212
  -4.250   0.0388   0.00888   0.00376  -0.1043   0.8611   0.0224
  -4.000   0.0650   0.00869   0.00351  -0.1038   0.8469   0.0232
  -3.750   0.0907   0.00858   0.00332  -0.1031   0.8238   0.0240
  -3.500   0.1134   0.00853   0.00304  -0.1018   0.7716   0.0245
  -3.250   0.1345   0.00864   0.00287  -0.1001   0.7125   0.0252
  -3.000   0.1572   0.00869   0.00270  -0.0989   0.6645   0.0259
  -2.750   0.1802   0.00872   0.00251  -0.0978   0.6132   0.0263
  -2.500   0.2038   0.00876   0.00232  -0.0968   0.5682   0.0266
  -2.250   0.2288   0.00873   0.00215  -0.0961   0.5408   0.0269
  -2.000   0.2544   0.00868   0.00199  -0.0955   0.5210   0.0272
  -1.750   0.2804   0.00862   0.00184  -0.0950   0.5057   0.0275
  -1.250   0.3332   0.00853   0.00162  -0.0941   0.4819   0.0283
  -1.000   0.3597   0.00849   0.00152  -0.0937   0.4716   0.0286
  -0.750   0.3862   0.00846   0.00144  -0.0933   0.4617   0.0289
  -0.500   0.4131   0.00843   0.00138  -0.0930   0.4532   0.0291
  -0.250   0.4397   0.00840   0.00129  -0.0926   0.4451   0.0303
   0.000   0.4664   0.00838   0.00123  -0.0922   0.4360   0.0323
   0.250   0.4931   0.00839   0.00121  -0.0918   0.4272   0.0341
   0.750   0.5464   0.00842   0.00120  -0.0911   0.4091   0.0390
   1.000   0.5728   0.00841   0.00123  -0.0907   0.4008   0.0633
   1.250   0.5993   0.00842   0.00127  -0.0903   0.3917   0.0822
   1.500   0.6255   0.00847   0.00131  -0.0899   0.3793   0.0957
   1.750   0.6506   0.00834   0.00139  -0.0894   0.3654   0.2111
   2.000   0.6763   0.00832   0.00148  -0.0890   0.3538   0.2749
   2.250   0.7011   0.00824   0.00158  -0.0885   0.3393   0.3790
   2.500   0.7191   0.00753   0.00176  -0.0867   0.3252   0.7639
   3.000   0.7944   0.00751   0.00202  -0.0911   0.2887   1.0000
   3.250   0.8198   0.00767   0.00213  -0.0905   0.2784   1.0000
   3.500   0.8450   0.00784   0.00224  -0.0899   0.2670   1.0000
   3.750   0.8698   0.00805   0.00237  -0.0893   0.2511   1.0000
   4.000   0.8945   0.00828   0.00252  -0.0886   0.2346   1.0000
   4.250   0.9194   0.00850   0.00266  -0.0880   0.2210   1.0000
   4.500   0.9441   0.00873   0.00283  -0.0874   0.2070   1.0000
   4.750   0.9685   0.00898   0.00301  -0.0867   0.1908   1.0000
   5.000   0.9920   0.00934   0.00324  -0.0859   0.1661   1.0000
   5.250   1.0127   0.00997   0.00362  -0.0847   0.1203   1.0000
   5.500   1.0354   0.01041   0.00394  -0.0838   0.1001   1.0000
   5.750   1.0596   0.01069   0.00419  -0.0831   0.0902   1.0000
   6.000   1.0834   0.01100   0.00444  -0.0824   0.0800   1.0000
   6.250   1.1068   0.01134   0.00472  -0.0816   0.0692   1.0000
   6.500   1.1302   0.01169   0.00501  -0.0809   0.0598   1.0000
   6.750   1.1538   0.01200   0.00529  -0.0801   0.0535   1.0000
   7.000   1.1771   0.01232   0.00559  -0.0794   0.0470   1.0000
   7.250   1.1970   0.01298   0.00609  -0.0781   0.0246   1.0000
   7.500   1.2178   0.01355   0.00662  -0.0769   0.0131   1.0000
   7.750   1.2399   0.01396   0.00706  -0.0759   0.0107   1.0000
   8.000   1.2622   0.01433   0.00748  -0.0749   0.0093   1.0000
   8.250   1.2845   0.01469   0.00788  -0.0740   0.0085   1.0000
   8.500   1.3061   0.01510   0.00832  -0.0730   0.0077   1.0000
   8.750   1.3263   0.01560   0.00887  -0.0718   0.0067   1.0000
   9.000   1.3475   0.01601   0.00931  -0.0707   0.0063   1.0000
   9.250   1.3680   0.01645   0.00980  -0.0695   0.0059   1.0000
   9.500   1.3878   0.01692   0.01032  -0.0683   0.0055   1.0000
   9.750   1.4069   0.01742   0.01086  -0.0669   0.0052   1.0000
  10.000   1.4246   0.01801   0.01150  -0.0653   0.0048   1.0000
  10.250   1.4406   0.01870   0.01225  -0.0635   0.0045   1.0000
  10.500   1.4579   0.01923   0.01284  -0.0619   0.0043   1.0000
  10.750   1.4730   0.01977   0.01345  -0.0599   0.0041   1.0000
  11.000   1.4866   0.02034   0.01408  -0.0576   0.0039   1.0000
  11.250   1.4994   0.02095   0.01474  -0.0553   0.0037   1.0000
  11.500   1.5108   0.02164   0.01550  -0.0528   0.0036   1.0000
  11.750   1.5216   0.02237   0.01630  -0.0504   0.0035   1.0000
  12.000   1.5319   0.02315   0.01713  -0.0480   0.0033   1.0000
  12.250   1.5394   0.02411   0.01817  -0.0453   0.0031   1.0000
  12.500   1.5451   0.02523   0.01938  -0.0426   0.0030   1.0000
  12.750   1.5485   0.02653   0.02078  -0.0398   0.0029   1.0000
  13.000   1.5546   0.02769   0.02205  -0.0376   0.0029   1.0000
  13.250   1.5591   0.02903   0.02348  -0.0353   0.0028   1.0000
  13.500   1.5622   0.03055   0.02510  -0.0332   0.0028   1.0000
  13.750   1.5629   0.03235   0.02701  -0.0312   0.0028   1.0000
  14.000   1.5636   0.03428   0.02905  -0.0296   0.0027   1.0000
  14.250   1.5638   0.03640   0.03127  -0.0282   0.0026   1.0000
  14.500   1.5613   0.03898   0.03397  -0.0273   0.0025   1.0000
  14.750   1.5553   0.04218   0.03730  -0.0268   0.0025   1.0000
  15.000   1.5502   0.04560   0.04084  -0.0269   0.0025   1.0000
  15.250   1.5421   0.04971   0.04508  -0.0276   0.0025   1.0000
  15.500   1.5333   0.05425   0.04975  -0.0289   0.0024   1.0000
  15.750   1.5255   0.05888   0.05451  -0.0305   0.0024   1.0000
  16.000   1.5091   0.06499   0.06077  -0.0328   0.0024   1.0000
  16.250   1.5041   0.06935   0.06522  -0.0344   0.0023   1.0000
  16.500   1.4835   0.07631   0.07233  -0.0372   0.0024   1.0000
  16.750   1.4666   0.08280   0.07895  -0.0399   0.0023   1.0000
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