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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 50,000
Max Cl/Cd: 41.14 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe335-il-50000-n5.txt
Download as CSV file: xf-goe335-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3134   0.10045   0.09405  -0.0257   1.0000   0.0777
  -7.250  -0.3192   0.09954   0.09329  -0.0275   1.0000   0.0791
  -7.000  -0.3202   0.09830   0.09216  -0.0305   1.0000   0.0797
  -6.750  -0.3162   0.09423   0.08819  -0.0296   1.0000   0.0809
  -6.500  -0.3099   0.09013   0.08415  -0.0264   1.0000   0.0835
  -6.250  -0.3072   0.08751   0.08161  -0.0259   1.0000   0.0862
  -6.000  -0.3054   0.08525   0.07942  -0.0265   1.0000   0.0895
  -5.750  -0.3024   0.08400   0.07823  -0.0306   1.0000   0.0933
  -5.500  -0.2951   0.08247   0.07670  -0.0352   1.0000   0.0943
  -5.250  -0.2967   0.07820   0.07256  -0.0304   1.0000   0.0959
  -5.000  -0.2950   0.07540   0.06982  -0.0281   1.0000   0.0987
  -4.750  -0.2897   0.07309   0.06752  -0.0283   1.0000   0.1036
  -4.250  -0.2703   0.06765   0.06206  -0.0306   0.9991   0.1162
  -4.000  -0.2328   0.06342   0.05765  -0.0381   0.9915   0.1268
  -3.500  -0.1388   0.05241   0.04594  -0.0538   0.9782   0.0749
  -3.250  -0.0988   0.04840   0.04161  -0.0592   0.9708   0.0750
  -3.000  -0.0542   0.04391   0.03668  -0.0648   0.9641   0.0704
  -2.750  -0.0089   0.03987   0.03208  -0.0697   0.9556   0.0689
  -2.500   0.0329   0.03715   0.02891  -0.0734   0.9445   0.0754
  -2.250   0.0786   0.03398   0.02513  -0.0772   0.9333   0.0751
  -2.000   0.1242   0.03128   0.02178  -0.0804   0.9219   0.0760
  -1.750   0.1679   0.02940   0.01946  -0.0834   0.9110   0.0840
  -1.500   0.2049   0.02778   0.01739  -0.0848   0.8995   0.0857
  -1.250   0.2430   0.02638   0.01557  -0.0863   0.8890   0.0866
  -1.000   0.2819   0.02515   0.01397  -0.0877   0.8792   0.0884
  -0.750   0.3233   0.02409   0.01252  -0.0893   0.8697   0.0911
  -0.500   0.3589   0.02327   0.01145  -0.0901   0.8579   0.0949
  -0.250   0.3936   0.02253   0.01062  -0.0908   0.8457   0.1020
   0.000   0.4275   0.02191   0.00990  -0.0914   0.8331   0.1168
   0.250   0.4605   0.02123   0.00936  -0.0920   0.8197   0.1575
   0.500   0.4972   0.01870   0.00879  -0.0932   0.8068   1.0000
   0.750   0.5277   0.01877   0.00844  -0.0930   0.7912   1.0000
   1.000   0.5570   0.01885   0.00824  -0.0926   0.7745   1.0000
   1.250   0.5854   0.01894   0.00811  -0.0921   0.7573   1.0000
   1.500   0.6113   0.01910   0.00809  -0.0913   0.7384   1.0000
   1.750   0.6369   0.01925   0.00809  -0.0904   0.7182   1.0000
   2.000   0.6636   0.01937   0.00806  -0.0896   0.6988   1.0000
   2.250   0.6882   0.01957   0.00816  -0.0886   0.6771   1.0000
   2.500   0.7142   0.01974   0.00820  -0.0878   0.6567   1.0000
   2.750   0.7393   0.01997   0.00833  -0.0869   0.6356   1.0000
   3.000   0.7647   0.02022   0.00849  -0.0861   0.6155   1.0000
   3.250   0.7906   0.02049   0.00868  -0.0854   0.5974   1.0000
   3.500   0.8154   0.02086   0.00898  -0.0847   0.5790   1.0000
   3.750   0.8405   0.02124   0.00931  -0.0841   0.5624   1.0000
   4.000   0.8659   0.02165   0.00973  -0.0835   0.5476   1.0000
   4.250   0.8913   0.02209   0.01016  -0.0830   0.5341   1.0000
   4.500   0.9168   0.02255   0.01062  -0.0825   0.5219   1.0000
   4.750   0.9427   0.02303   0.01116  -0.0821   0.5108   1.0000
   5.000   0.9674   0.02359   0.01182  -0.0816   0.4996   1.0000
   5.250   0.9923   0.02418   0.01250  -0.0811   0.4895   1.0000
   5.500   1.0179   0.02474   0.01313  -0.0807   0.4802   1.0000
   5.750   1.0422   0.02536   0.01394  -0.0801   0.4699   1.0000
   6.000   1.0657   0.02602   0.01475  -0.0794   0.4592   1.0000
   6.250   1.0899   0.02666   0.01554  -0.0788   0.4491   1.0000
   6.500   1.1144   0.02732   0.01636  -0.0782   0.4397   1.0000
   6.750   1.1367   0.02814   0.01752  -0.0774   0.4302   1.0000
   7.000   1.1613   0.02889   0.01850  -0.0769   0.4220   1.0000
   7.250   1.1838   0.02964   0.01951  -0.0759   0.4112   1.0000
   7.500   1.1988   0.02997   0.02000  -0.0736   0.3873   1.0000
   7.750   1.2121   0.03019   0.02032  -0.0709   0.3610   1.0000
   8.000   1.2253   0.03056   0.02088  -0.0685   0.3377   1.0000
   8.250   1.2314   0.03098   0.02155  -0.0651   0.3049   1.0000
   8.500   1.2313   0.03168   0.02233  -0.0614   0.2467   1.0000
   8.750   1.2246   0.03355   0.02347  -0.0574   0.1481   1.0000
   9.000   1.2108   0.03699   0.02614  -0.0538   0.0805   1.0000
   9.500   1.1973   0.04285   0.03203  -0.0483   0.0530   1.0000
   9.750   1.1899   0.04596   0.03521  -0.0465   0.0478   1.0000
  10.000   1.1843   0.04911   0.03854  -0.0453   0.0442   1.0000
  10.250   1.1762   0.05276   0.04232  -0.0448   0.0414   1.0000
  10.500   1.1672   0.05677   0.04642  -0.0447   0.0398   1.0000
  10.750   1.1610   0.06068   0.05056  -0.0448   0.0381   1.0000
  11.000   1.1551   0.06470   0.05477  -0.0451   0.0369   1.0000
  11.250   1.1503   0.06869   0.05892  -0.0455   0.0358   1.0000
  11.500   1.1467   0.07257   0.06295  -0.0458   0.0348   1.0000
  11.750   1.1441   0.07636   0.06685  -0.0461   0.0337   1.0000
  12.000   1.1425   0.07997   0.07054  -0.0462   0.0326   1.0000
  12.250   1.1445   0.08312   0.07380  -0.0458   0.0313   1.0000
  12.500   1.1492   0.08608   0.07703  -0.0452   0.0298   1.0000
  12.750   1.1535   0.08922   0.08041  -0.0448   0.0285   1.0000
  13.000   1.1583   0.09243   0.08386  -0.0444   0.0276   1.0000
  13.250   1.1622   0.09601   0.08769  -0.0443   0.0271   1.0000
  13.500   1.1627   0.10030   0.09235  -0.0449   0.0267   1.0000
  13.750   1.1595   0.10530   0.09762  -0.0464   0.0265   1.0000
  14.000   1.1532   0.11098   0.10355  -0.0486   0.0265   1.0000
  14.250   1.1442   0.11737   0.11018  -0.0517   0.0265   1.0000
  14.500   1.1330   0.12453   0.11757  -0.0556   0.0267   1.0000
  14.750   1.1195   0.13259   0.12585  -0.0603   0.0269   1.0000
  15.000   1.1049   0.14146   0.13490  -0.0657   0.0273   1.0000
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