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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 200,000
Max Cl/Cd: 75.36 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe335-il-200000.txt
Download as CSV file: xf-goe335-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 335 (D.F.W.) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3214   0.08843   0.08519  -0.0226   1.0000   0.0302
  -7.000  -0.3244   0.08633   0.08316  -0.0217   1.0000   0.0307
  -6.750  -0.3239   0.08388   0.08077  -0.0219   1.0000   0.0314
  -6.500  -0.3234   0.08149   0.07843  -0.0221   1.0000   0.0320
  -6.250  -0.3232   0.07915   0.07615  -0.0223   1.0000   0.0327
  -6.000  -0.3254   0.07708   0.07415  -0.0220   1.0000   0.0333
  -5.750  -0.3341   0.07566   0.07278  -0.0204   1.0000   0.0339
  -5.500  -0.2794   0.07105   0.06801  -0.0369   0.9940   0.0368
  -5.250  -0.2259   0.06595   0.06271  -0.0492   0.9868   0.0373
  -5.000  -0.2064   0.05855   0.05534  -0.0528   0.9818   0.0390
  -4.750  -0.1788   0.05525   0.05203  -0.0555   0.9746   0.0419
  -4.500  -0.1336   0.05078   0.04741  -0.0635   0.9700   0.0461
  -4.250  -0.0754   0.04521   0.04133  -0.0742   0.9607   0.0508
  -4.000  -0.0475   0.04128   0.03748  -0.0770   0.9566   0.0533
  -3.750  -0.0142   0.03847   0.03456  -0.0799   0.9476   0.0587
  -3.500   0.0303   0.03451   0.03031  -0.0852   0.9430   0.0678
  -3.250   0.0701   0.03156   0.02689  -0.0884   0.9332   0.0790
  -3.000   0.1083   0.03046   0.02552  -0.0905   0.9258   0.0912
  -2.750   0.1350   0.02678   0.02191  -0.0921   0.9165   0.0970
  -2.500   0.1668   0.02486   0.01978  -0.0933   0.9062   0.1109
  -2.250   0.1997   0.02304   0.01775  -0.0946   0.8964   0.1255
  -2.000   0.2413   0.01866   0.01229  -0.0947   0.8874   0.0800
  -1.750   0.2729   0.01665   0.00995  -0.0947   0.8757   0.0709
  -1.500   0.3043   0.01503   0.00784  -0.0944   0.8641   0.0668
  -1.250   0.3340   0.01411   0.00671  -0.0943   0.8521   0.0670
  -1.000   0.3624   0.01358   0.00609  -0.0940   0.8395   0.0707
  -0.750   0.3901   0.01297   0.00534  -0.0935   0.8265   0.0715
  -0.500   0.4169   0.01249   0.00475  -0.0928   0.8131   0.0730
  -0.250   0.4430   0.01213   0.00432  -0.0920   0.7993   0.0757
   0.000   0.4684   0.01176   0.00392  -0.0912   0.7854   0.0796
   0.250   0.4937   0.01153   0.00369  -0.0904   0.7710   0.0875
   0.500   0.5188   0.01130   0.00348  -0.0895   0.7555   0.1073
   0.750   0.5578   0.00901   0.00326  -0.0918   0.7383   1.0000
   1.000   0.5823   0.00909   0.00315  -0.0907   0.7190   1.0000
   1.250   0.6066   0.00917   0.00307  -0.0896   0.6971   1.0000
   1.500   0.6306   0.00928   0.00300  -0.0885   0.6721   1.0000
   1.750   0.6542   0.00942   0.00296  -0.0873   0.6418   1.0000
   2.000   0.6775   0.00962   0.00295  -0.0861   0.6066   1.0000
   2.250   0.7005   0.00990   0.00298  -0.0850   0.5708   1.0000
   2.500   0.7238   0.01021   0.00309  -0.0839   0.5391   1.0000
   2.750   0.7475   0.01054   0.00322  -0.0830   0.5148   1.0000
   3.000   0.7718   0.01087   0.00339  -0.0823   0.4960   1.0000
   3.250   0.7965   0.01121   0.00360  -0.0817   0.4810   1.0000
   3.500   0.8214   0.01155   0.00386  -0.0811   0.4681   1.0000
   3.750   0.8463   0.01190   0.00412  -0.0806   0.4564   1.0000
   4.000   0.8715   0.01227   0.00439  -0.0801   0.4464   1.0000
   4.250   0.8968   0.01257   0.00469  -0.0796   0.4365   1.0000
   4.500   0.9222   0.01293   0.00504  -0.0792   0.4281   1.0000
   4.750   0.9476   0.01326   0.00537  -0.0787   0.4196   1.0000
   5.000   0.9727   0.01358   0.00572  -0.0783   0.4107   1.0000
   5.250   0.9980   0.01398   0.00607  -0.0778   0.4028   1.0000
   5.500   1.0227   0.01423   0.00643  -0.0773   0.3937   1.0000
   5.750   1.0467   0.01452   0.00677  -0.0766   0.3825   1.0000
   6.000   1.0704   0.01478   0.00706  -0.0759   0.3708   1.0000
   6.250   1.0928   0.01492   0.00727  -0.0749   0.3545   1.0000
   6.500   1.1158   0.01513   0.00754  -0.0740   0.3412   1.0000
   6.750   1.1387   0.01531   0.00784  -0.0731   0.3265   1.0000
   7.000   1.1597   0.01542   0.00800  -0.0719   0.3004   1.0000
   7.250   1.1802   0.01566   0.00821  -0.0706   0.2536   1.0000
   7.500   1.1844   0.01780   0.00935  -0.0675   0.0977   1.0000
   7.750   1.1916   0.01995   0.01103  -0.0646   0.0403   1.0000
   8.000   1.2065   0.02116   0.01229  -0.0626   0.0323   1.0000
   8.250   1.2214   0.02226   0.01359  -0.0606   0.0298   1.0000
   8.500   1.2343   0.02344   0.01493  -0.0584   0.0281   1.0000
   8.750   1.2443   0.02475   0.01638  -0.0558   0.0269   1.0000
   9.000   1.2517   0.02619   0.01792  -0.0529   0.0260   1.0000
   9.250   1.2555   0.02771   0.01954  -0.0496   0.0252   1.0000
   9.500   1.2582   0.02941   0.02130  -0.0463   0.0245   1.0000
   9.750   1.2599   0.03173   0.02368  -0.0432   0.0234   1.0000
  10.000   1.2694   0.03387   0.02591  -0.0410   0.0225   1.0000
  10.250   1.2837   0.03582   0.02801  -0.0395   0.0223   1.0000
  10.500   1.3015   0.03815   0.03051  -0.0383   0.0221   1.0000
  10.750   1.3211   0.04099   0.03356  -0.0375   0.0221   1.0000
  11.000   1.3406   0.04468   0.03750  -0.0370   0.0224   1.0000
  11.250   1.3658   0.04951   0.04259  -0.0375   0.0232   1.0000
  11.500   1.3688   0.05064   0.04394  -0.0344   0.0237   1.0000
  11.750   1.3621   0.05303   0.04684  -0.0304   0.0256   1.0000
  12.000   1.3460   0.05821   0.05254  -0.0271   0.0279   1.0000
  12.250   1.3341   0.06263   0.05725  -0.0253   0.0291   1.0000
  12.500   1.3197   0.06773   0.06259  -0.0242   0.0301   1.0000
  13.750   1.0972   0.09294   0.08912  -0.0282   0.0293   1.0000
  14.000   1.0676   0.09959   0.09596  -0.0321   0.0291   1.0000
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