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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 500,000
Max Cl/Cd: 102.1 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe335-il-500000.txt
Download as CSV file: xf-goe335-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3265   0.08784   0.08576  -0.0217   1.0000   0.0160
  -7.250  -0.3313   0.08601   0.08397  -0.0203   1.0000   0.0163
  -7.000  -0.3365   0.08405   0.08207  -0.0191   1.0000   0.0167
  -6.750  -0.3374   0.08167   0.07973  -0.0191   1.0000   0.0172
  -6.500  -0.3111   0.07730   0.07535  -0.0278   0.9970   0.0189
  -6.250  -0.2659   0.07171   0.06969  -0.0423   0.9914   0.0194
  -6.000  -0.2298   0.06641   0.06432  -0.0511   0.9862   0.0195
  -5.750  -0.1930   0.06091   0.05875  -0.0595   0.9814   0.0196
  -5.500  -0.1676   0.05349   0.05127  -0.0665   0.9738   0.0201
  -5.250  -0.1371   0.05032   0.04806  -0.0705   0.9695   0.0209
  -5.000  -0.1067   0.04711   0.04479  -0.0746   0.9593   0.0221
  -4.750  -0.0679   0.04307   0.04061  -0.0804   0.9482   0.0248
  -4.500  -0.0181   0.03911   0.03638  -0.0865   0.9348   0.0268
  -4.250   0.0190   0.03428   0.03127  -0.0906   0.9158   0.0269
  -4.000   0.0440   0.02752   0.02417  -0.0941   0.8902   0.0286
  -3.750   0.0707   0.02622   0.02269  -0.0948   0.8649   0.0302
  -3.500   0.0970   0.02442   0.02060  -0.0950   0.8455   0.0337
  -3.250   0.1285   0.02390   0.01963  -0.0942   0.8311   0.0374
  -3.000   0.1482   0.01908   0.01447  -0.0945   0.8193   0.0405
  -2.750   0.1733   0.01811   0.01332  -0.0942   0.8081   0.0434
  -2.500   0.1997   0.01669   0.01159  -0.0936   0.7978   0.0467
  -2.250   0.2266   0.01312   0.00726  -0.0924   0.7884   0.0395
  -2.000   0.2530   0.01212   0.00604  -0.0919   0.7780   0.0393
  -1.750   0.2793   0.01139   0.00519  -0.0914   0.7682   0.0411
  -1.250   0.3322   0.01028   0.00386  -0.0904   0.7478   0.0430
  -1.000   0.3585   0.00986   0.00336  -0.0899   0.7369   0.0437
  -0.750   0.3847   0.00951   0.00294  -0.0894   0.7253   0.0444
  -0.500   0.4108   0.00926   0.00262  -0.0889   0.7124   0.0460
  -0.250   0.4368   0.00901   0.00231  -0.0883   0.6980   0.0472
   0.000   0.4628   0.00882   0.00205  -0.0877   0.6820   0.0485
   0.250   0.4888   0.00870   0.00186  -0.0872   0.6643   0.0499
   0.750   0.5399   0.00854   0.00152  -0.0859   0.6198   0.0598
   1.000   0.5647   0.00845   0.00149  -0.0852   0.5896   0.1178
   1.250   0.6005   0.00671   0.00165  -0.0876   0.5459   1.0000
   1.500   0.6234   0.00703   0.00169  -0.0865   0.4983   1.0000
   1.750   0.6466   0.00736   0.00178  -0.0856   0.4624   1.0000
   2.000   0.6710   0.00763   0.00188  -0.0849   0.4405   1.0000
   2.250   0.6959   0.00786   0.00199  -0.0843   0.4248   1.0000
   2.500   0.7211   0.00807   0.00211  -0.0837   0.4136   1.0000
   2.750   0.7463   0.00828   0.00224  -0.0832   0.4040   1.0000
   3.000   0.7721   0.00844   0.00236  -0.0828   0.3956   1.0000
   3.250   0.7974   0.00865   0.00250  -0.0822   0.3871   1.0000
   3.500   0.8233   0.00881   0.00265  -0.0819   0.3792   1.0000
   3.750   0.8487   0.00901   0.00281  -0.0814   0.3724   1.0000
   4.000   0.8747   0.00915   0.00295  -0.0810   0.3655   1.0000
   4.250   0.8999   0.00938   0.00313  -0.0805   0.3593   1.0000
   4.500   0.9262   0.00950   0.00330  -0.0802   0.3533   1.0000
   4.750   0.9513   0.00971   0.00347  -0.0797   0.3447   1.0000
   5.000   0.9772   0.00983   0.00362  -0.0794   0.3350   1.0000
   5.250   1.0027   0.01000   0.00379  -0.0790   0.3254   1.0000
   5.500   1.0278   0.01021   0.00399  -0.0785   0.3162   1.0000
   5.750   1.0530   0.01038   0.00416  -0.0780   0.3032   1.0000
   6.000   1.0782   0.01056   0.00434  -0.0776   0.2871   1.0000
   6.250   1.1028   0.01081   0.00454  -0.0771   0.2635   1.0000
   6.500   1.1223   0.01157   0.00491  -0.0759   0.1911   1.0000
   6.750   1.1309   0.01361   0.00619  -0.0732   0.0666   1.0000
   7.000   1.1472   0.01482   0.00714  -0.0715   0.0218   1.0000
   7.250   1.1685   0.01545   0.00784  -0.0704   0.0189   1.0000
   7.500   1.1883   0.01623   0.00873  -0.0690   0.0168   1.0000
   7.750   1.2061   0.01717   0.00982  -0.0673   0.0157   1.0000
   8.000   1.2249   0.01793   0.01069  -0.0659   0.0150   1.0000
   8.250   1.2425   0.01875   0.01161  -0.0643   0.0141   1.0000
   8.500   1.2583   0.01968   0.01262  -0.0625   0.0133   1.0000
   8.750   1.2719   0.02073   0.01377  -0.0604   0.0127   1.0000
   9.000   1.2834   0.02188   0.01501  -0.0580   0.0122   1.0000
   9.250   1.2915   0.02322   0.01643  -0.0552   0.0118   1.0000
   9.500   1.2955   0.02464   0.01793  -0.0517   0.0115   1.0000
   9.750   1.2967   0.02637   0.01977  -0.0480   0.0112   1.0000
  10.000   1.2996   0.02852   0.02200  -0.0448   0.0110   1.0000
  10.250   1.3095   0.03063   0.02420  -0.0427   0.0109   1.0000
  10.500   1.3272   0.03353   0.02721  -0.0418   0.0108   1.0000
  10.750   1.3361   0.03552   0.02938  -0.0398   0.0105   1.0000
  11.000   1.3367   0.03586   0.02988  -0.0367   0.0102   1.0000
  11.250   1.3440   0.03778   0.03195  -0.0348   0.0100   1.0000
  11.500   1.3496   0.03990   0.03425  -0.0329   0.0098   1.0000
  11.750   1.3541   0.04276   0.03731  -0.0312   0.0100   1.0000
  12.000   1.3544   0.04559   0.04034  -0.0295   0.0099   1.0000
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