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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.81 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe257-il-1000000-n5.txt
Download as CSV file: xf-goe257-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4471   0.09583   0.09431  -0.0119   1.0000   0.0055
  -8.750  -0.4508   0.08933   0.08783  -0.0163   0.9641   0.0058
  -8.500  -0.4497   0.08615   0.08459  -0.0178   0.9307   0.0059
  -8.250  -0.4459   0.08294   0.08128  -0.0201   0.9014   0.0060
  -8.000  -0.4368   0.07959   0.07780  -0.0235   0.8655   0.0062
  -7.750  -0.4264   0.07598   0.07393  -0.0274   0.7930   0.0064
  -7.250  -0.4006   0.06079   0.05834  -0.0442   0.7310   0.0079
  -6.750  -0.3574   0.05183   0.04909  -0.0529   0.7063   0.0085
  -6.500  -0.3335   0.04830   0.04543  -0.0559   0.6971   0.0090
  -6.250  -0.3076   0.03685   0.03352  -0.0626   0.6910   0.0110
  -5.750  -0.2536   0.02321   0.01887  -0.0666   0.6777   0.0146
  -5.500  -0.2260   0.02307   0.01866  -0.0670   0.6701   0.0149
  -5.250  -0.1985   0.02293   0.01846  -0.0673   0.6631   0.0151
  -5.000  -0.1708   0.02232   0.01773  -0.0677   0.6573   0.0154
  -4.750  -0.1427   0.02129   0.01657  -0.0682   0.6525   0.0160
  -4.500  -0.1141   0.01973   0.01478  -0.0686   0.6471   0.0171
  -4.250  -0.0844   0.01708   0.01164  -0.0689   0.6423   0.0188
  -4.000  -0.0555   0.01676   0.01118  -0.0692   0.6370   0.0192
  -3.750  -0.0270   0.01496   0.00910  -0.0697   0.6317   0.0198
  -3.500   0.0016   0.01430   0.00834  -0.0701   0.6270   0.0200
  -3.250   0.0304   0.01375   0.00771  -0.0704   0.6223   0.0203
  -3.000   0.0592   0.01326   0.00714  -0.0708   0.6171   0.0206
  -2.750   0.0880   0.01294   0.00674  -0.0711   0.6123   0.0210
  -2.500   0.1170   0.01248   0.00622  -0.0714   0.6073   0.0214
  -2.250   0.1459   0.01202   0.00568  -0.0716   0.6015   0.0218
  -2.000   0.1748   0.01164   0.00521  -0.0719   0.5949   0.0223
  -1.750   0.2037   0.01129   0.00479  -0.0721   0.5858   0.0228
  -1.500   0.2325   0.01100   0.00444  -0.0724   0.5754   0.0233
  -1.250   0.2614   0.01074   0.00410  -0.0727   0.5641   0.0236
  -1.000   0.2902   0.01050   0.00380  -0.0729   0.5531   0.0238
  -0.750   0.3190   0.01027   0.00352  -0.0732   0.5420   0.0240
  -0.500   0.3478   0.01008   0.00327  -0.0735   0.5274   0.0241
  -0.250   0.3765   0.00997   0.00308  -0.0737   0.5082   0.0244
   0.000   0.4051   0.00992   0.00295  -0.0740   0.4876   0.0247
   0.250   0.4338   0.00982   0.00277  -0.0743   0.4721   0.0248
   0.500   0.4626   0.00973   0.00262  -0.0746   0.4587   0.0248
   0.750   0.4913   0.00967   0.00251  -0.0749   0.4460   0.0249
   1.000   0.5201   0.00964   0.00242  -0.0752   0.4343   0.0250
   1.250   0.5488   0.00962   0.00237  -0.0755   0.4251   0.0252
   1.500   0.5776   0.00961   0.00234  -0.0758   0.4170   0.0254
   1.750   0.6063   0.00959   0.00226  -0.0761   0.4052   0.0264
   2.000   0.6350   0.00960   0.00223  -0.0764   0.3953   0.0279
   2.250   0.6637   0.00962   0.00224  -0.0766   0.3875   0.0289
   2.500   0.6922   0.00969   0.00228  -0.0769   0.3771   0.0298
   2.750   0.7207   0.00976   0.00232  -0.0772   0.3653   0.0306
   3.000   0.7491   0.00985   0.00238  -0.0774   0.3511   0.0313
   3.250   0.7773   0.01001   0.00246  -0.0777   0.3297   0.0328
   3.500   0.8045   0.01036   0.00262  -0.0779   0.2832   0.0336
   3.750   0.8312   0.01085   0.00289  -0.0780   0.2347   0.0362
   4.250   0.8817   0.00950   0.00340  -0.0780   0.1979   1.0000
   4.500   0.9092   0.00980   0.00360  -0.0782   0.1798   1.0000
   4.750   0.9364   0.01012   0.00381  -0.0783   0.1605   1.0000
   5.000   0.9615   0.01088   0.00424  -0.0783   0.0983   1.0000
   5.250   0.9869   0.01154   0.00471  -0.0783   0.0551   1.0000
   5.500   1.0137   0.01187   0.00500  -0.0783   0.0450   1.0000
   5.750   1.0403   0.01221   0.00529  -0.0784   0.0340   1.0000
   6.000   1.0661   0.01270   0.00568  -0.0783   0.0151   1.0000
   6.250   1.0928   0.01298   0.00598  -0.0783   0.0125   1.0000
   6.500   1.1191   0.01331   0.00633  -0.0783   0.0109   1.0000
   6.750   1.1450   0.01370   0.00676  -0.0782   0.0093   1.0000
   7.000   1.1709   0.01405   0.00715  -0.0781   0.0085   1.0000
   7.250   1.1967   0.01440   0.00752  -0.0780   0.0078   1.0000
   7.500   1.2221   0.01477   0.00792  -0.0778   0.0071   1.0000
   7.750   1.2470   0.01521   0.00838  -0.0776   0.0064   1.0000
   8.000   1.2707   0.01579   0.00901  -0.0772   0.0059   1.0000
   8.250   1.2951   0.01622   0.00949  -0.0769   0.0056   1.0000
   8.500   1.3189   0.01671   0.01003  -0.0765   0.0053   1.0000
   8.750   1.3421   0.01724   0.01060  -0.0760   0.0050   1.0000
   9.000   1.3649   0.01777   0.01119  -0.0755   0.0047   1.0000
   9.250   1.3873   0.01830   0.01176  -0.0750   0.0044   1.0000
   9.500   1.4087   0.01891   0.01240  -0.0743   0.0041   1.0000
   9.750   1.4267   0.01983   0.01339  -0.0730   0.0038   1.0000
  10.000   1.4464   0.02049   0.01412  -0.0721   0.0037   1.0000
  10.250   1.4648   0.02122   0.01494  -0.0709   0.0036   1.0000
  10.500   1.4815   0.02201   0.01581  -0.0695   0.0035   1.0000
  10.750   1.4963   0.02287   0.01676  -0.0678   0.0034   1.0000
  11.000   1.5091   0.02379   0.01776  -0.0658   0.0033   1.0000
  11.250   1.5200   0.02476   0.01881  -0.0636   0.0031   1.0000
  11.500   1.5256   0.02581   0.01995  -0.0605   0.0031   1.0000
  11.750   1.5298   0.02701   0.02124  -0.0575   0.0030   1.0000
  12.000   1.5346   0.02836   0.02267  -0.0550   0.0029   1.0000
  12.250   1.5387   0.02993   0.02435  -0.0529   0.0028   1.0000
  12.500   1.5436   0.03159   0.02609  -0.0512   0.0028   1.0000
  12.750   1.5471   0.03352   0.02812  -0.0497   0.0027   1.0000
  13.000   1.5500   0.03569   0.03038  -0.0486   0.0027   1.0000
  13.250   1.5515   0.03818   0.03298  -0.0479   0.0026   1.0000
  13.500   1.5514   0.04105   0.03596  -0.0475   0.0026   1.0000
  13.750   1.5494   0.04429   0.03931  -0.0473   0.0025   1.0000
  14.000   1.5441   0.04797   0.04311  -0.0473   0.0025   1.0000
  14.250   1.5359   0.05209   0.04737  -0.0474   0.0024   1.0000
  14.500   1.5248   0.05662   0.05204  -0.0476   0.0024   1.0000
  14.750   1.5144   0.06112   0.05667  -0.0479   0.0024   1.0000
  15.000   1.5066   0.06543   0.06111  -0.0485   0.0023   1.0000
  15.250   1.4991   0.06983   0.06563  -0.0493   0.0023   1.0000
  15.500   1.4911   0.07444   0.07037  -0.0502   0.0023   1.0000
  15.750   1.4830   0.07925   0.07530  -0.0514   0.0023   1.0000
  16.000   1.4740   0.08432   0.08049  -0.0528   0.0023   1.0000
  16.250   1.4644   0.08958   0.08588  -0.0544   0.0023   1.0000
  16.500   1.4548   0.09496   0.09138  -0.0561   0.0022   1.0000
  16.750   1.4449   0.10049   0.09702  -0.0580   0.0022   1.0000
  17.000   1.4336   0.10632   0.10298  -0.0600   0.0022   1.0000
  17.250   1.4219   0.11230   0.10908  -0.0623   0.0022   1.0000
  17.500   1.4105   0.11837   0.11527  -0.0647   0.0022   1.0000
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