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GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 491 AIRFOIL (goe491-il)
Reynolds number: 200,000
Max Cl/Cd: 62.8 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe491-il-200000.txt
Download as CSV file: xf-goe491-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 491 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4900   0.10580   0.10216  -0.0033   1.0000   0.0325
  -8.500  -0.4925   0.10391   0.10034  -0.0068   1.0000   0.0328
  -8.250  -0.4928   0.10123   0.09770  -0.0090   1.0000   0.0329
  -8.000  -0.4901   0.09824   0.09474  -0.0117   1.0000   0.0330
  -7.750  -0.4836   0.09486   0.09136  -0.0145   1.0000   0.0330
  -7.500  -0.4810   0.08945   0.08598  -0.0158   1.0000   0.0334
  -7.250  -0.4773   0.08438   0.08095  -0.0122   1.0000   0.0342
  -7.000  -0.4703   0.08096   0.07755  -0.0117   1.0000   0.0349
  -6.750  -0.4630   0.07765   0.07424  -0.0122   1.0000   0.0358
  -6.500  -0.4545   0.07438   0.07095  -0.0134   1.0000   0.0368
  -6.250  -0.4447   0.07101   0.06756  -0.0149   1.0000   0.0381
  -6.000  -0.4331   0.06761   0.06413  -0.0166   1.0000   0.0395
  -5.750  -0.4180   0.06418   0.06064  -0.0188   1.0000   0.0417
  -5.500  -0.3879   0.06183   0.05800  -0.0237   1.0000   0.0439
  -5.250  -0.3700   0.05872   0.05472  -0.0242   1.0000   0.0442
  -5.000  -0.3613   0.05281   0.04874  -0.0243   1.0000   0.0448
  -4.750  -0.3521   0.04890   0.04487  -0.0232   1.0000   0.0458
  -4.500  -0.3391   0.04602   0.04198  -0.0221   1.0000   0.0470
  -4.250  -0.3237   0.04344   0.03934  -0.0212   1.0000   0.0496
  -4.000  -0.2925   0.04258   0.03796  -0.0209   1.0000   0.0569
  -3.750  -0.2807   0.03745   0.03266  -0.0198   1.0000   0.0581
  -3.500  -0.2668   0.03438   0.02958  -0.0185   1.0000   0.0594
  -3.250  -0.2505   0.03203   0.02714  -0.0169   1.0000   0.0610
  -3.000  -0.2282   0.02620   0.02061  -0.0141   1.0000   0.0424
  -2.750  -0.2099   0.02287   0.01690  -0.0120   1.0000   0.0406
  -2.500  -0.1889   0.02032   0.01387  -0.0099   1.0000   0.0424
  -2.250  -0.1670   0.01804   0.01107  -0.0081   1.0000   0.0450
  -2.000  -0.1457   0.01664   0.00954  -0.0068   1.0000   0.0486
  -1.750  -0.1232   0.01580   0.00844  -0.0053   1.0000   0.0555
  -1.500  -0.1017   0.01515   0.00771  -0.0042   1.0000   0.0665
  -1.250  -0.0796   0.01444   0.00687  -0.0030   1.0000   0.0771
  -1.000  -0.0460   0.01409   0.00647  -0.0045   0.9964   0.0909
  -0.750  -0.0020   0.01372   0.00595  -0.0078   0.9891   0.0986
  -0.500   0.0411   0.01282   0.00514  -0.0110   0.9824   0.1055
  -0.250   0.0830   0.01228   0.00460  -0.0138   0.9729   0.1110
   0.000   0.1230   0.01165   0.00407  -0.0162   0.9623   0.1173
   0.250   0.1638   0.01112   0.00364  -0.0188   0.9509   0.1297
   0.500   0.2050   0.01057   0.00324  -0.0213   0.9389   0.1519
   0.750   0.3066   0.00827   0.00319  -0.0371   0.9437   1.0000
   1.000   0.3601   0.00806   0.00290  -0.0421   0.9196   1.0000
   1.250   0.4183   0.00786   0.00256  -0.0480   0.8736   1.0000
   1.500   0.4502   0.00794   0.00242  -0.0481   0.8040   1.0000
   1.750   0.4733   0.00818   0.00235  -0.0464   0.7288   1.0000
   2.000   0.4940   0.00854   0.00236  -0.0444   0.6619   1.0000
   2.250   0.5149   0.00891   0.00244  -0.0427   0.6084   1.0000
   2.500   0.5364   0.00925   0.00256  -0.0412   0.5658   1.0000
   2.750   0.5576   0.00960   0.00267  -0.0397   0.5236   1.0000
   3.000   0.5792   0.00993   0.00284  -0.0383   0.4868   1.0000
   3.250   0.6018   0.01023   0.00302  -0.0372   0.4614   1.0000
   3.500   0.6247   0.01052   0.00323  -0.0361   0.4397   1.0000
   3.750   0.6478   0.01079   0.00346  -0.0351   0.4177   1.0000
   4.000   0.6707   0.01106   0.00371  -0.0340   0.3953   1.0000
   4.250   0.6938   0.01127   0.00393  -0.0330   0.3693   1.0000
   4.500   0.7167   0.01150   0.00415  -0.0319   0.3394   1.0000
   4.750   0.7392   0.01177   0.00436  -0.0308   0.2963   1.0000
   5.000   0.7591   0.01240   0.00465  -0.0294   0.2150   1.0000
   5.250   0.7744   0.01385   0.00541  -0.0275   0.0932   1.0000
   5.500   0.7943   0.01476   0.00621  -0.0259   0.0714   1.0000
   5.750   0.8148   0.01553   0.00702  -0.0245   0.0629   1.0000
   6.000   0.8342   0.01642   0.00794  -0.0229   0.0563   1.0000
   6.250   0.8531   0.01744   0.00905  -0.0212   0.0523   1.0000
   6.500   0.8724   0.01841   0.01005  -0.0196   0.0467   1.0000
   6.750   0.8878   0.02055   0.01222  -0.0175   0.0431   1.0000
   7.000   0.9090   0.02173   0.01358  -0.0160   0.0405   1.0000
   7.250   0.9291   0.02308   0.01505  -0.0145   0.0364   1.0000
   7.500   0.9488   0.02506   0.01715  -0.0131   0.0343   1.0000
   7.750   0.9675   0.02805   0.02034  -0.0116   0.0328   1.0000
   8.000   0.9828   0.03207   0.02476  -0.0097   0.0320   1.0000
   8.250   0.9958   0.03396   0.02712  -0.0074   0.0302   1.0000
   8.500   1.0086   0.03633   0.02994  -0.0051   0.0292   1.0000
   8.750   1.0160   0.04004   0.03408  -0.0026   0.0295   1.0000
   9.000   1.0177   0.04463   0.03909   0.0000   0.0302   1.0000
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