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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.5 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe335-il-1000000.txt
Download as CSV file: xf-goe335-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3340   0.09133   0.08981  -0.0224   1.0000   0.0104
  -7.750  -0.3378   0.08896   0.08747  -0.0217   1.0000   0.0104
  -7.500  -0.3442   0.08679   0.08534  -0.0206   0.9998   0.0104
  -7.250  -0.3264   0.08050   0.07906  -0.0274   0.9969   0.0108
  -7.000  -0.3023   0.07701   0.07556  -0.0328   0.9938   0.0111
  -6.750  -0.2787   0.07343   0.07197  -0.0384   0.9893   0.0116
  -6.500  -0.2497   0.06904   0.06756  -0.0461   0.9846   0.0123
  -6.250  -0.2150   0.06370   0.06218  -0.0566   0.9763   0.0141
  -5.000  -0.0662   0.01326   0.00918  -0.0947   0.8507   0.0149
  -4.750  -0.0397   0.01407   0.00998  -0.0943   0.8293   0.0155
  -4.500  -0.0124   0.01511   0.01106  -0.0940   0.8147   0.0160
  -4.250   0.0136   0.01499   0.01085  -0.0936   0.8026   0.0169
  -4.000   0.0385   0.01337   0.00887  -0.0930   0.7921   0.0186
  -3.750   0.0654   0.01331   0.00868  -0.0927   0.7822   0.0195
  -3.500   0.0897   0.01173   0.00681  -0.0922   0.7731   0.0213
  -3.250   0.1168   0.01187   0.00696  -0.0921   0.7637   0.0224
  -3.000   0.1434   0.01153   0.00651  -0.0918   0.7548   0.0238
  -2.750   0.1701   0.01109   0.00594  -0.0914   0.7456   0.0252
  -2.500   0.1973   0.01097   0.00574  -0.0911   0.7363   0.0263
  -2.250   0.2233   0.01001   0.00456  -0.0907   0.7269   0.0280
  -2.000   0.2494   0.00922   0.00366  -0.0903   0.7165   0.0291
  -1.750   0.2760   0.00885   0.00323  -0.0899   0.7048   0.0304
  -1.500   0.3027   0.00866   0.00297  -0.0896   0.6919   0.0320
  -1.250   0.3292   0.00840   0.00263  -0.0892   0.6779   0.0330
  -1.000   0.3556   0.00815   0.00231  -0.0887   0.6634   0.0337
  -0.750   0.3818   0.00795   0.00202  -0.0883   0.6475   0.0342
  -0.500   0.4080   0.00779   0.00177  -0.0878   0.6299   0.0347
  -0.250   0.4342   0.00768   0.00157  -0.0874   0.6094   0.0354
   0.000   0.4602   0.00766   0.00144  -0.0869   0.5844   0.0364
   0.250   0.4859   0.00769   0.00132  -0.0864   0.5507   0.0370
   0.500   0.5106   0.00778   0.00119  -0.0857   0.5036   0.0387
   0.750   0.5352   0.00795   0.00114  -0.0851   0.4577   0.0418
   1.000   0.5608   0.00809   0.00115  -0.0846   0.4292   0.0450
   1.250   0.5870   0.00817   0.00116  -0.0842   0.4112   0.0502
   1.500   0.6126   0.00800   0.00126  -0.0839   0.3990   0.1781
   1.750   0.6494   0.00640   0.00150  -0.0866   0.3880   1.0000
   2.000   0.6755   0.00651   0.00155  -0.0861   0.3799   1.0000
   2.250   0.7013   0.00664   0.00161  -0.0857   0.3718   1.0000
   2.500   0.7273   0.00676   0.00169  -0.0853   0.3631   1.0000
   2.750   0.7534   0.00688   0.00176  -0.0849   0.3558   1.0000
   3.000   0.7795   0.00700   0.00184  -0.0845   0.3497   1.0000
   3.250   0.8055   0.00713   0.00194  -0.0841   0.3440   1.0000
   3.500   0.8319   0.00724   0.00203  -0.0838   0.3374   1.0000
   3.750   0.8577   0.00739   0.00214  -0.0834   0.3313   1.0000
   4.000   0.8842   0.00748   0.00224  -0.0831   0.3262   1.0000
   4.500   0.9363   0.00775   0.00247  -0.0824   0.3093   1.0000
   4.750   0.9620   0.00791   0.00260  -0.0820   0.3013   1.0000
   5.000   0.9882   0.00804   0.00272  -0.0817   0.2936   1.0000
   5.250   1.0139   0.00821   0.00286  -0.0813   0.2818   1.0000
   5.500   1.0389   0.00844   0.00303  -0.0809   0.2628   1.0000
   5.750   1.0627   0.00879   0.00323  -0.0803   0.2321   1.0000
   6.000   1.0801   0.00981   0.00380  -0.0787   0.1538   1.0000
   6.250   1.0943   0.01124   0.00470  -0.0767   0.0566   1.0000
   6.500   1.1132   0.01219   0.00541  -0.0752   0.0159   1.0000
   6.750   1.1371   0.01254   0.00583  -0.0745   0.0146   1.0000
   7.000   1.1601   0.01298   0.00632  -0.0737   0.0131   1.0000
   7.250   1.1819   0.01356   0.00697  -0.0727   0.0116   1.0000
   7.500   1.2023   0.01427   0.00778  -0.0715   0.0105   1.0000
   7.750   1.2248   0.01470   0.00825  -0.0706   0.0099   1.0000
   8.000   1.2460   0.01526   0.00888  -0.0696   0.0093   1.0000
   8.250   1.2662   0.01588   0.00957  -0.0684   0.0088   1.0000
   8.500   1.2856   0.01654   0.01029  -0.0671   0.0084   1.0000
   8.750   1.3036   0.01728   0.01109  -0.0656   0.0079   1.0000
   9.000   1.3181   0.01829   0.01218  -0.0636   0.0075   1.0000
   9.250   1.3160   0.02054   0.01460  -0.0591   0.0070   1.0000
   9.500   1.3309   0.02134   0.01549  -0.0572   0.0069   1.0000
   9.750   1.3494   0.02180   0.01600  -0.0559   0.0066   1.0000
  10.000   1.3596   0.02266   0.01694  -0.0532   0.0064   1.0000
  10.250   1.3677   0.02356   0.01791  -0.0503   0.0062   1.0000
  10.500   1.3742   0.02460   0.01903  -0.0474   0.0060   1.0000
  10.750   1.3780   0.02593   0.02045  -0.0442   0.0058   1.0000
  11.000   1.3839   0.02714   0.02175  -0.0417   0.0057   1.0000
  11.250   1.3866   0.02876   0.02347  -0.0390   0.0056   1.0000
  11.500   1.3921   0.03014   0.02494  -0.0370   0.0054   1.0000
  11.750   1.3938   0.03211   0.02701  -0.0348   0.0054   1.0000
  12.000   1.3982   0.03373   0.02873  -0.0333   0.0052   1.0000
  12.250   1.4007   0.03577   0.03086  -0.0318   0.0052   1.0000
  12.500   1.4021   0.03799   0.03319  -0.0306   0.0050   1.0000
  12.750   1.4045   0.04005   0.03532  -0.0298   0.0049   1.0000
  13.000   1.4035   0.04283   0.03822  -0.0289   0.0049   1.0000
  13.250   1.4017   0.04577   0.04128  -0.0282   0.0048   1.0000
  13.500   1.3951   0.04957   0.04520  -0.0275   0.0046   1.0000
  13.750   1.3883   0.05354   0.04934  -0.0272   0.0046   1.0000
  14.000   1.3641   0.06048   0.05660  -0.0273   0.0044   1.0000
  14.500   1.3500   0.06857   0.06498  -0.0300   0.0043   1.0000
  15.000   1.3223   0.08029   0.07704  -0.0343   0.0044   1.0000
  15.250   1.3120   0.08598   0.08288  -0.0373   0.0043   1.0000
  15.500   1.2971   0.09282   0.08988  -0.0407   0.0043   1.0000
  15.750   1.2873   0.09906   0.09626  -0.0443   0.0042   1.0000
  16.250   1.2497   0.11576   0.11328  -0.0535   0.0043   1.0000
  16.500   1.2346   0.12386   0.12152  -0.0584   0.0043   1.0000
  16.750   1.0669   0.13287   0.13088  -0.0650   0.0046   1.0000
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