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GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 269 AIRFOIL (goe269-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.9 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe269-il-1000000.txt
Download as CSV file: xf-goe269-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 269 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3834   0.10139   0.09979  -0.0107   1.0000   0.0172
  -8.500  -0.3782   0.09783   0.09624  -0.0126   1.0000   0.0172
  -8.250  -0.3756   0.09359   0.09201  -0.0137   1.0000   0.0175
  -8.000  -0.3657   0.09151   0.08995  -0.0141   1.0000   0.0177
  -7.750  -0.3571   0.08941   0.08786  -0.0149   1.0000   0.0181
  -7.500  -0.3479   0.08700   0.08547  -0.0164   1.0000   0.0185
  -6.500  -0.2643   0.06728   0.06568  -0.0446   0.9627   0.0217
  -6.250  -0.2436   0.06526   0.06360  -0.0463   0.9397   0.0220
  -6.000  -0.2238   0.06297   0.06123  -0.0485   0.9192   0.0225
  -5.750  -0.2016   0.06025   0.05842  -0.0517   0.9028   0.0234
  -5.500  -0.1592   0.05435   0.05234  -0.0628   0.8886   0.0259
  -5.250  -0.1310   0.04737   0.04520  -0.0700   0.8758   0.0264
  -5.000  -0.1086   0.04560   0.04336  -0.0710   0.8610   0.0268
  -4.750  -0.0842   0.04383   0.04150  -0.0724   0.8442   0.0272
  -4.500  -0.0573   0.04178   0.03934  -0.0744   0.8255   0.0280
  -4.250  -0.0153   0.03806   0.03536  -0.0795   0.8064   0.0314
  -3.250   0.1212   0.01232   0.00737  -0.0938   0.7400   0.0314
  -3.000   0.1506   0.01051   0.00512  -0.0943   0.7254   0.0323
  -2.750   0.1792   0.01000   0.00448  -0.0945   0.7125   0.0333
  -2.500   0.2079   0.00970   0.00409  -0.0945   0.7009   0.0340
  -2.250   0.2366   0.00942   0.00372  -0.0945   0.6906   0.0346
  -1.750   0.2941   0.00892   0.00306  -0.0946   0.6724   0.0361
  -1.500   0.3227   0.00872   0.00277  -0.0946   0.6638   0.0370
  -1.250   0.3516   0.00854   0.00256  -0.0947   0.6554   0.0378
  -1.000   0.3803   0.00835   0.00229  -0.0947   0.6479   0.0388
  -0.750   0.4092   0.00814   0.00207  -0.0948   0.6398   0.0414
  -0.500   0.4378   0.00811   0.00202  -0.0948   0.6317   0.0434
  -0.250   0.4665   0.00806   0.00195  -0.0948   0.6234   0.0455
   0.000   0.4953   0.00795   0.00183  -0.0948   0.6157   0.0491
   0.250   0.5238   0.00798   0.00187  -0.0948   0.6067   0.0529
   0.500   0.5523   0.00805   0.00192  -0.0948   0.5975   0.0557
   0.750   0.5809   0.00801   0.00187  -0.0948   0.5856   0.0606
   1.000   0.6092   0.00809   0.00192  -0.0948   0.5717   0.0643
   1.250   0.6374   0.00818   0.00198  -0.0947   0.5554   0.0666
   1.500   0.6659   0.00810   0.00185  -0.0948   0.5359   0.0706
   1.750   0.6940   0.00818   0.00185  -0.0948   0.5109   0.0736
   2.000   0.7218   0.00833   0.00189  -0.0948   0.4800   0.0767
   2.250   0.7493   0.00854   0.00197  -0.0947   0.4507   0.0789
   2.500   0.7773   0.00862   0.00197  -0.0947   0.4298   0.0818
   2.750   0.8053   0.00869   0.00201  -0.0947   0.4150   0.0854
   3.000   0.8333   0.00879   0.00207  -0.0947   0.4035   0.0883
   3.250   0.8614   0.00887   0.00213  -0.0947   0.3932   0.0910
   3.500   0.8894   0.00895   0.00220  -0.0947   0.3837   0.0936
   3.750   0.9173   0.00905   0.00230  -0.0947   0.3740   0.1014
   4.000   0.9453   0.00910   0.00240  -0.0947   0.3651   0.1218
   4.250   0.9683   0.00772   0.00269  -0.0941   0.3561   1.0000
   4.500   0.9960   0.00789   0.00280  -0.0941   0.3452   1.0000
   4.750   1.0238   0.00803   0.00292  -0.0940   0.3355   1.0000
   5.000   1.0513   0.00822   0.00306  -0.0940   0.3236   1.0000
   5.250   1.0785   0.00844   0.00321  -0.0939   0.3071   1.0000
   5.500   1.1054   0.00870   0.00339  -0.0938   0.2869   1.0000
   5.750   1.1321   0.00900   0.00359  -0.0936   0.2646   1.0000
   6.000   1.1579   0.00943   0.00385  -0.0934   0.2311   1.0000
   6.250   1.1827   0.01001   0.00421  -0.0931   0.1908   1.0000
   6.500   1.2075   0.01058   0.00460  -0.0928   0.1591   1.0000
   6.750   1.2328   0.01103   0.00495  -0.0925   0.1413   1.0000
   7.000   1.2586   0.01138   0.00525  -0.0923   0.1302   1.0000
   7.250   1.2844   0.01171   0.00556  -0.0920   0.1208   1.0000
   7.500   1.3098   0.01208   0.00589  -0.0917   0.1114   1.0000
   7.750   1.3352   0.01243   0.00621  -0.0914   0.1022   1.0000
   8.000   1.3605   0.01278   0.00654  -0.0911   0.0926   1.0000
   8.250   1.3848   0.01325   0.00693  -0.0907   0.0781   1.0000
   8.500   1.4067   0.01403   0.00752  -0.0900   0.0538   1.0000
   8.750   1.4252   0.01523   0.00848  -0.0888   0.0236   1.0000
   9.000   1.4466   0.01599   0.00921  -0.0880   0.0175   1.0000
   9.250   1.4694   0.01653   0.00980  -0.0873   0.0159   1.0000
   9.500   1.4914   0.01714   0.01044  -0.0865   0.0147   1.0000
   9.750   1.5117   0.01792   0.01128  -0.0854   0.0134   1.0000
  10.000   1.5323   0.01861   0.01204  -0.0844   0.0127   1.0000
  10.250   1.5532   0.01922   0.01271  -0.0835   0.0122   1.0000
  10.500   1.5730   0.01989   0.01344  -0.0825   0.0116   1.0000
  10.750   1.5918   0.02061   0.01421  -0.0813   0.0111   1.0000
  11.000   1.6081   0.02151   0.01518  -0.0798   0.0105   1.0000
  11.250   1.6164   0.02305   0.01685  -0.0772   0.0099   1.0000
  11.500   1.6323   0.02379   0.01765  -0.0756   0.0097   1.0000
  11.750   1.6457   0.02461   0.01855  -0.0737   0.0095   1.0000
  12.000   1.6548   0.02554   0.01956  -0.0712   0.0093   1.0000
  12.250   1.6610   0.02661   0.02072  -0.0683   0.0090   1.0000
  12.500   1.6667   0.02785   0.02205  -0.0658   0.0088   1.0000
  12.750   1.6718   0.02927   0.02355  -0.0636   0.0086   1.0000
  13.000   1.6759   0.03091   0.02529  -0.0617   0.0084   1.0000
  13.250   1.6792   0.03275   0.02722  -0.0601   0.0082   1.0000
  13.500   1.6811   0.03488   0.02944  -0.0587   0.0080   1.0000
  13.750   1.6803   0.03743   0.03208  -0.0576   0.0079   1.0000
  14.000   1.6760   0.04057   0.03534  -0.0568   0.0077   1.0000
  14.250   1.6679   0.04437   0.03926  -0.0565   0.0076   1.0000
  14.500   1.6553   0.04893   0.04397  -0.0565   0.0075   1.0000
  14.750   1.6378   0.05425   0.04944  -0.0568   0.0074   1.0000
  15.000   1.6276   0.05880   0.05411  -0.0573   0.0073   1.0000
  15.250   1.6242   0.06255   0.05798  -0.0580   0.0072   1.0000
  15.500   1.6187   0.06665   0.06219  -0.0587   0.0072   1.0000
  15.750   1.6106   0.07129   0.06695  -0.0598   0.0071   1.0000
  16.000   1.6030   0.07603   0.07181  -0.0611   0.0070   1.0000
  16.250   1.5941   0.08108   0.07697  -0.0626   0.0070   1.0000
  16.500   1.5837   0.08650   0.08250  -0.0643   0.0069   1.0000
  16.750   1.5721   0.09222   0.08834  -0.0663   0.0069   1.0000
  17.000   1.5608   0.09794   0.09417  -0.0683   0.0068   1.0000
  17.250   1.5484   0.10393   0.10028  -0.0705   0.0068   1.0000
  17.500   1.5362   0.10997   0.10643  -0.0729   0.0067   1.0000
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