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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.65 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe92-il-1000000.txt
Download as CSV file: xf-goe92-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1895   0.09358   0.09197  -0.0296   0.9061   0.0084
  -9.000  -0.1872   0.09027   0.08862  -0.0308   0.8973   0.0084
  -8.750  -0.1844   0.08691   0.08524  -0.0319   0.8894   0.0085
  -8.500  -0.1809   0.08359   0.08189  -0.0329   0.8825   0.0085
  -8.250  -0.1774   0.08020   0.07849  -0.0340   0.8755   0.0085
  -8.000  -0.1737   0.07682   0.07509  -0.0351   0.8695   0.0085
  -7.250  -0.1607   0.06649   0.06473  -0.0365   0.8501   0.0090
  -7.000  -0.1558   0.06348   0.06170  -0.0377   0.8432   0.0093
  -6.750  -0.1508   0.06026   0.05849  -0.0395   0.8356   0.0095
  -6.500  -0.1424   0.05666   0.05485  -0.0426   0.8280   0.0097
  -6.250  -0.1308   0.05277   0.05095  -0.0463   0.8197   0.0100
  -6.000  -0.1588   0.06459   0.06265  -0.0525   0.8347   0.0097
  -5.750  -0.1366   0.06094   0.05894  -0.0569   0.8267   0.0100
  -5.500  -0.1123   0.05716   0.05509  -0.0614   0.8176   0.0106
  -5.250  -0.0777   0.05271   0.05052  -0.0678   0.8085   0.0115
  -5.000  -0.0470   0.04854   0.04621  -0.0724   0.7979   0.0116
  -4.750  -0.0192   0.04465   0.04218  -0.0753   0.7850   0.0116
  -4.500   0.0049   0.03932   0.03667  -0.0784   0.7702   0.0119
  -4.250   0.0267   0.03744   0.03467  -0.0793   0.7458   0.0123
  -4.000   0.0514   0.03544   0.03246  -0.0803   0.7073   0.0130
  -3.750   0.0854   0.03291   0.02953  -0.0811   0.6615   0.0152
  -3.250   0.1413   0.02773   0.02374  -0.0819   0.6056   0.0154
  -2.750   0.1921   0.02163   0.01710  -0.0828   0.5721   0.0163
  -2.500   0.2181   0.02089   0.01622  -0.0830   0.5562   0.0175
  -2.250   0.2494   0.02023   0.01527  -0.0821   0.5418   0.0202
  -2.000   0.2772   0.01837   0.01310  -0.0819   0.5282   0.0203
  -1.750   0.3040   0.01486   0.00914  -0.0817   0.5158   0.0213
  -1.500   0.3303   0.01464   0.00889  -0.0819   0.4999   0.0226
  -1.250   0.3587   0.01544   0.00956  -0.0816   0.4827   0.0267
  -1.000   0.3866   0.01474   0.00860  -0.0813   0.4644   0.0270
  -0.750   0.4135   0.01237   0.00586  -0.0811   0.4441   0.0284
  -0.500   0.4401   0.01192   0.00530  -0.0810   0.4173   0.0299
  -0.250   0.4669   0.01169   0.00491  -0.0809   0.3938   0.0320
   0.000   0.4946   0.01251   0.00560  -0.0807   0.3754   0.0359
   1.000   0.6033   0.01025   0.00300  -0.0800   0.3386   0.0346
   1.250   0.6308   0.00995   0.00268  -0.0799   0.3341   0.0340
   1.500   0.6582   0.00980   0.00249  -0.0798   0.3294   0.0343
   1.750   0.6855   0.00976   0.00241  -0.0797   0.3247   0.0350
   2.000   0.7132   0.00971   0.00234  -0.0797   0.3216   0.0354
   2.250   0.7408   0.00968   0.00230  -0.0797   0.3180   0.0357
   2.500   0.7683   0.00970   0.00229  -0.0797   0.3144   0.0360
   2.750   0.7955   0.00973   0.00228  -0.0796   0.3102   0.0368
   3.000   0.8232   0.00973   0.00228  -0.0796   0.3074   0.0374
   3.250   0.8509   0.00976   0.00229  -0.0796   0.3048   0.0395
   3.500   0.8784   0.00981   0.00234  -0.0796   0.3020   0.0454
   3.750   0.9038   0.00818   0.00266  -0.0798   0.2993   1.0000
   4.000   0.9306   0.00835   0.00278  -0.0797   0.2960   1.0000
   4.250   0.9580   0.00846   0.00288  -0.0796   0.2935   1.0000
   4.500   0.9854   0.00854   0.00296  -0.0797   0.2896   1.0000
   4.750   1.0121   0.00872   0.00307  -0.0796   0.2815   1.0000
   5.000   1.0394   0.00881   0.00317  -0.0796   0.2776   1.0000
   5.250   1.0664   0.00894   0.00327  -0.0796   0.2704   1.0000
   5.500   1.0932   0.00909   0.00339  -0.0795   0.2612   1.0000
   5.750   1.1196   0.00928   0.00354  -0.0795   0.2498   1.0000
   6.000   1.1449   0.00960   0.00372  -0.0792   0.2260   1.0000
   6.250   1.1609   0.01103   0.00457  -0.0779   0.1330   1.0000
   6.500   1.1815   0.01193   0.00521  -0.0770   0.0950   1.0000
   6.750   1.1976   0.01338   0.00632  -0.0755   0.0166   1.0000
   7.000   1.2218   0.01380   0.00678  -0.0751   0.0139   1.0000
   7.250   1.2453   0.01428   0.00734  -0.0745   0.0119   1.0000
   7.500   1.2690   0.01470   0.00781  -0.0741   0.0112   1.0000
   7.750   1.2920   0.01520   0.00837  -0.0735   0.0104   1.0000
   8.000   1.3142   0.01575   0.00899  -0.0728   0.0097   1.0000
   8.250   1.3354   0.01640   0.00970  -0.0720   0.0091   1.0000
   8.500   1.3527   0.01741   0.01083  -0.0706   0.0082   1.0000
   8.750   1.3688   0.01846   0.01199  -0.0691   0.0077   1.0000
   9.000   1.3882   0.01912   0.01272  -0.0681   0.0074   1.0000
   9.250   1.4050   0.01995   0.01364  -0.0667   0.0071   1.0000
   9.500   1.4197   0.02088   0.01465  -0.0651   0.0068   1.0000
   9.750   1.4320   0.02191   0.01576  -0.0632   0.0065   1.0000
  10.000   1.4399   0.02295   0.01688  -0.0606   0.0063   1.0000
  10.250   1.4457   0.02413   0.01814  -0.0580   0.0061   1.0000
  10.500   1.4504   0.02547   0.01957  -0.0556   0.0058   1.0000
  10.750   1.4529   0.02710   0.02129  -0.0534   0.0057   1.0000
  11.000   1.4519   0.02918   0.02345  -0.0515   0.0055   1.0000
  11.250   1.4471   0.03179   0.02616  -0.0497   0.0054   1.0000
  11.500   1.4368   0.03517   0.02964  -0.0481   0.0053   1.0000
  11.750   1.4224   0.03925   0.03383  -0.0469   0.0052   1.0000
  12.000   1.4088   0.04341   0.03808  -0.0458   0.0050   1.0000
  12.250   1.4163   0.04570   0.04048  -0.0463   0.0049   1.0000
  12.500   1.4185   0.04860   0.04348  -0.0466   0.0048   1.0000
  12.750   1.4169   0.05188   0.04686  -0.0466   0.0047   1.0000
  13.000   1.4143   0.05521   0.05027  -0.0465   0.0046   1.0000
  13.250   1.4124   0.05843   0.05357  -0.0463   0.0046   1.0000
  13.500   1.4111   0.06150   0.05673  -0.0459   0.0045   1.0000
  13.750   1.4109   0.06439   0.05970  -0.0453   0.0045   1.0000
  14.000   1.4116   0.06723   0.06261  -0.0448   0.0044   1.0000
  14.250   1.4125   0.07006   0.06552  -0.0442   0.0044   1.0000
  14.500   1.4132   0.07297   0.06853  -0.0438   0.0043   1.0000
  14.750   1.4140   0.07588   0.07153  -0.0431   0.0043   1.0000
  15.000   1.4127   0.07936   0.07513  -0.0434   0.0041   1.0000
  15.250   1.4111   0.08279   0.07868  -0.0432   0.0041   1.0000
  15.500   1.4078   0.08660   0.08261  -0.0434   0.0041   1.0000
  15.750   1.4027   0.09080   0.08695  -0.0438   0.0040   1.0000
  16.000   1.3962   0.09523   0.09155  -0.0434   0.0043   1.0000
  16.250   1.3847   0.10057   0.09704  -0.0439   0.0046   1.0000
  17.500   1.0843   0.11870   0.11591  -0.0367   0.0045   1.0000
  17.750   1.0707   0.12282   0.12015  -0.0385   0.0045   1.0000
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