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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.25 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe585-il-1000000.txt
Download as CSV file: xf-goe585-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.3536   0.13976   0.13808  -0.0172   1.0000   0.0126
 -13.250  -0.3490   0.13725   0.13557  -0.0179   1.0000   0.0128
 -13.000  -0.4726   0.14273   0.14093  -0.0087   1.0000   0.0123
 -12.750  -0.4662   0.13983   0.13803  -0.0095   1.0000   0.0124
 -12.500  -0.4583   0.13761   0.13582  -0.0101   1.0000   0.0128
 -12.250  -0.4525   0.13461   0.13282  -0.0111   1.0000   0.0130
 -12.000  -0.4474   0.13133   0.12955  -0.0121   1.0000   0.0133
  -9.500  -0.7288   0.02609   0.02334  -0.0599   0.9983   0.0149
  -9.250  -0.7011   0.02388   0.02084  -0.0618   0.9965   0.0153
  -9.000  -0.6758   0.02074   0.01730  -0.0637   0.9946   0.0161
  -8.750  -0.6434   0.02087   0.01747  -0.0648   0.9934   0.0164
  -8.500  -0.6125   0.02076   0.01735  -0.0656   0.9914   0.0168
  -8.250  -0.5807   0.02074   0.01733  -0.0665   0.9896   0.0174
  -8.000  -0.5498   0.02003   0.01651  -0.0676   0.9877   0.0181
  -7.750  -0.5186   0.01914   0.01543  -0.0688   0.9861   0.0189
  -7.500  -0.4852   0.01886   0.01503  -0.0701   0.9849   0.0194
  -7.250  -0.4571   0.01625   0.01211  -0.0715   0.9836   0.0204
  -7.000  -0.4303   0.01589   0.01173  -0.0714   0.9797   0.0210
  -6.750  -0.3991   0.01569   0.01151  -0.0722   0.9772   0.0217
  -6.500  -0.3670   0.01526   0.01103  -0.0733   0.9753   0.0226
  -6.250  -0.3344   0.01461   0.01025  -0.0744   0.9737   0.0234
  -6.000  -0.3008   0.01412   0.00966  -0.0756   0.9725   0.0241
  -5.750  -0.2659   0.01397   0.00943  -0.0770   0.9714   0.0245
  -5.500  -0.2423   0.01193   0.00719  -0.0766   0.9662   0.0259
  -5.250  -0.2115   0.01143   0.00666  -0.0773   0.9626   0.0268
  -5.000  -0.1793   0.01092   0.00609  -0.0782   0.9595   0.0274
  -4.750  -0.1481   0.01044   0.00557  -0.0788   0.9537   0.0282
  -4.500  -0.1169   0.01002   0.00510  -0.0793   0.9453   0.0291
  -4.250  -0.0876   0.00960   0.00460  -0.0794   0.9353   0.0297
  -4.000  -0.0579   0.00921   0.00415  -0.0796   0.9262   0.0302
  -3.750  -0.0300   0.00892   0.00379  -0.0794   0.9154   0.0307
  -3.500  -0.0030   0.00870   0.00351  -0.0790   0.9042   0.0310
  -3.250   0.0222   0.00811   0.00282  -0.0783   0.8923   0.0322
  -3.000   0.0481   0.00780   0.00243  -0.0777   0.8797   0.0332
  -2.750   0.0743   0.00758   0.00216  -0.0771   0.8672   0.0340
  -2.500   0.1004   0.00741   0.00193  -0.0765   0.8536   0.0348
  -2.250   0.1265   0.00728   0.00173  -0.0759   0.8387   0.0358
  -2.000   0.1525   0.00716   0.00155  -0.0753   0.8214   0.0370
  -1.750   0.1784   0.00708   0.00140  -0.0746   0.8016   0.0382
  -1.500   0.2041   0.00704   0.00126  -0.0739   0.7805   0.0397
  -1.250   0.2295   0.00697   0.00112  -0.0732   0.7594   0.0448
  -1.000   0.2547   0.00685   0.00104  -0.0724   0.7400   0.0720
  -0.750   0.2800   0.00676   0.00101  -0.0718   0.7219   0.1102
  -0.500   0.3057   0.00672   0.00098  -0.0712   0.7051   0.1376
  -0.250   0.3316   0.00666   0.00096  -0.0706   0.6896   0.1663
   0.000   0.3564   0.00649   0.00097  -0.0700   0.6731   0.2463
   0.250   0.3815   0.00637   0.00099  -0.0694   0.6547   0.3213
   0.500   0.4061   0.00619   0.00101  -0.0687   0.6356   0.4138
   0.750   0.4203   0.00525   0.00107  -0.0660   0.6164   0.7740
   1.000   0.4779   0.00508   0.00121  -0.0722   0.5817   0.9791
   1.250   0.5203   0.00536   0.00127  -0.0754   0.5318   0.9944
   1.500   0.5609   0.00574   0.00133  -0.0783   0.4655   1.0000
   1.750   0.5826   0.00600   0.00141  -0.0770   0.4275   1.0000
   2.000   0.6052   0.00622   0.00150  -0.0758   0.4001   1.0000
   2.250   0.6285   0.00641   0.00158  -0.0748   0.3781   1.0000
   2.500   0.6519   0.00659   0.00167  -0.0738   0.3595   1.0000
   2.750   0.6755   0.00676   0.00176  -0.0728   0.3431   1.0000
   3.250   0.7232   0.00710   0.00196  -0.0710   0.3140   1.0000
   3.500   0.7474   0.00725   0.00207  -0.0702   0.3022   1.0000
   3.750   0.7716   0.00740   0.00218  -0.0693   0.2911   1.0000
   4.000   0.7957   0.00758   0.00230  -0.0685   0.2790   1.0000
   4.250   0.8196   0.00777   0.00244  -0.0676   0.2653   1.0000
   4.750   0.8677   0.00814   0.00271  -0.0660   0.2417   1.0000
   5.000   0.8918   0.00832   0.00286  -0.0652   0.2305   1.0000
   5.250   0.9158   0.00852   0.00302  -0.0643   0.2208   1.0000
   5.500   0.9398   0.00872   0.00319  -0.0635   0.2113   1.0000
   5.750   0.9640   0.00891   0.00335  -0.0628   0.2016   1.0000
   6.000   0.9879   0.00914   0.00354  -0.0620   0.1910   1.0000
   6.250   1.0116   0.00937   0.00374  -0.0612   0.1812   1.0000
   6.500   1.0359   0.00957   0.00393  -0.0604   0.1725   1.0000
   6.750   1.0596   0.00982   0.00415  -0.0597   0.1618   1.0000
   7.000   1.0830   0.01010   0.00438  -0.0588   0.1500   1.0000
   7.250   1.1060   0.01040   0.00464  -0.0580   0.1359   1.0000
   7.500   1.1279   0.01082   0.00495  -0.0569   0.1148   1.0000
   7.750   1.1472   0.01147   0.00540  -0.0555   0.0840   1.0000
   8.000   1.1668   0.01209   0.00591  -0.0542   0.0639   1.0000
   8.250   1.1879   0.01259   0.00634  -0.0530   0.0523   1.0000
   8.500   1.2089   0.01308   0.00679  -0.0519   0.0420   1.0000
   8.750   1.2283   0.01372   0.00733  -0.0505   0.0282   1.0000
   9.000   1.2477   0.01434   0.00792  -0.0492   0.0205   1.0000
   9.250   1.2678   0.01489   0.00847  -0.0479   0.0178   1.0000
   9.500   1.2876   0.01545   0.00906  -0.0466   0.0159   1.0000
   9.750   1.3079   0.01593   0.00959  -0.0453   0.0149   1.0000
  10.000   1.3268   0.01650   0.01020  -0.0440   0.0139   1.0000
  10.250   1.3434   0.01725   0.01101  -0.0422   0.0129   1.0000
  10.500   1.3601   0.01793   0.01178  -0.0404   0.0123   1.0000
  10.750   1.3779   0.01848   0.01239  -0.0389   0.0118   1.0000
  11.000   1.3940   0.01911   0.01308  -0.0371   0.0113   1.0000
  11.250   1.4089   0.01974   0.01377  -0.0352   0.0109   1.0000
  11.500   1.4202   0.02043   0.01453  -0.0326   0.0105   1.0000
  11.750   1.4285   0.02126   0.01542  -0.0296   0.0100   1.0000
  12.000   1.4281   0.02258   0.01685  -0.0256   0.0096   1.0000
  12.250   1.4341   0.02359   0.01796  -0.0227   0.0094   1.0000
  12.500   1.4441   0.02441   0.01885  -0.0205   0.0092   1.0000
  12.750   1.4524   0.02535   0.01987  -0.0183   0.0090   1.0000
  13.000   1.4573   0.02656   0.02117  -0.0158   0.0088   1.0000
  13.250   1.4631   0.02778   0.02249  -0.0138   0.0085   1.0000
  13.500   1.4658   0.02929   0.02409  -0.0117   0.0084   1.0000
  13.750   1.4690   0.03086   0.02575  -0.0099   0.0082   1.0000
  14.000   1.4721   0.03256   0.02753  -0.0085   0.0080   1.0000
  14.250   1.4734   0.03451   0.02958  -0.0072   0.0079   1.0000
  14.500   1.4713   0.03697   0.03214  -0.0063   0.0077   1.0000
  14.750   1.4680   0.03974   0.03501  -0.0057   0.0076   1.0000
  15.000   1.4628   0.04294   0.03833  -0.0056   0.0076   1.0000
  15.250   1.4547   0.04672   0.04221  -0.0060   0.0074   1.0000
  15.500   1.4438   0.05112   0.04673  -0.0069   0.0073   1.0000
  15.750   1.4300   0.05619   0.05194  -0.0085   0.0072   1.0000
  16.000   1.4148   0.06182   0.05770  -0.0105   0.0072   1.0000
  16.250   1.4000   0.06770   0.06371  -0.0129   0.0072   1.0000
  16.500   1.3855   0.07374   0.06988  -0.0156   0.0071   1.0000
  16.750   1.3671   0.08054   0.07681  -0.0186   0.0071   1.0000
  17.000   1.3502   0.08717   0.08357  -0.0216   0.0070   1.0000
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