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GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il)
Reynolds number: 50,000
Max Cl/Cd: 22.47 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe256-il-50000-n5.txt
Download as CSV file: xf-goe256-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 256 (JUNKERS E) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3046   0.10655   0.09947  -0.0652   0.9617   0.1023
  -8.750  -0.2815   0.10346   0.09633  -0.0655   0.9584   0.1001
  -8.500  -0.2743   0.09980   0.09265  -0.0674   0.9533   0.0979
  -8.000  -0.3384   0.08640   0.07911  -0.0771   0.9327   0.0894
  -7.750  -0.3327   0.08264   0.07529  -0.0785   0.9272   0.0890
  -7.500  -0.3367   0.07880   0.07134  -0.0791   0.9207   0.0889
  -7.250  -0.3440   0.07504   0.06741  -0.0789   0.9133   0.0890
  -7.000  -0.3427   0.07031   0.06236  -0.0806   0.9081   0.0893
  -6.750  -0.3504   0.06729   0.05908  -0.0785   0.9002   0.0895
  -6.500  -0.3389   0.06470   0.05642  -0.0782   0.8950   0.0902
  -6.250  -0.3234   0.06127   0.05268  -0.0792   0.8908   0.0904
  -6.000  -0.3214   0.05896   0.05013  -0.0769   0.8836   0.0906
  -5.750  -0.3079   0.05651   0.04743  -0.0763   0.8779   0.0911
  -5.500  -0.2842   0.05435   0.04506  -0.0772   0.8737   0.0926
  -5.250  -0.2737   0.05279   0.04329  -0.0755   0.8669   0.0943
  -5.000  -0.2565   0.05090   0.04108  -0.0748   0.8606   0.0963
  -4.750  -0.2295   0.04864   0.03838  -0.0757   0.8563   0.0983
  -4.500  -0.2143   0.04706   0.03642  -0.0742   0.8493   0.0994
  -4.250  -0.1921   0.04546   0.03430  -0.0737   0.8429   0.1016
  -4.000  -0.1594   0.04403   0.03277  -0.0751   0.8386   0.1048
  -3.750  -0.1427   0.04327   0.03191  -0.0736   0.8306   0.1073
  -3.500  -0.1144   0.04215   0.03054  -0.0738   0.8244   0.1101
  -3.250  -0.0762   0.04094   0.02893  -0.0754   0.8204   0.1148
  -3.000  -0.0624   0.04041   0.02832  -0.0734   0.8107   0.1178
  -2.750  -0.0280   0.03948   0.02733  -0.0745   0.8054   0.1221
  -2.500  -0.0016   0.03891   0.02661  -0.0742   0.7983   0.1270
  -2.250   0.0250   0.03837   0.02591  -0.0739   0.7906   0.1323
  -2.000   0.0658   0.03745   0.02500  -0.0758   0.7865   0.1388
  -1.750   0.0824   0.03738   0.02483  -0.0740   0.7762   0.1448
  -1.500   0.1208   0.03666   0.02408  -0.0755   0.7709   0.1535
  -1.250   0.1438   0.03643   0.02379  -0.0746   0.7624   0.1617
  -1.000   0.1732   0.03594   0.02334  -0.0748   0.7551   0.1734
  -0.750   0.2135   0.03506   0.02252  -0.0764   0.7512   0.1920
  -0.500   0.2245   0.03514   0.02274  -0.0739   0.7390   0.2109
  -0.250   0.2606   0.03392   0.02211  -0.0749   0.7346   0.3040
   0.000   0.3922   0.03188   0.02195  -0.0924   0.7344   1.0000
   0.250   0.3973   0.03236   0.02225  -0.0886   0.7217   1.0000
   0.500   0.4342   0.03198   0.02161  -0.0895   0.7165   1.0000
   0.750   0.4379   0.03252   0.02202  -0.0855   0.7035   1.0000
   1.000   0.4759   0.03209   0.02137  -0.0866   0.6984   1.0000
   1.500   0.5169   0.03224   0.02123  -0.0836   0.6802   1.0000
   1.750   0.5162   0.03295   0.02185  -0.0790   0.6662   1.0000
   2.250   0.5550   0.03321   0.02188  -0.0758   0.6478   1.0000
   2.500   0.5610   0.03386   0.02245  -0.0724   0.6357   1.0000
   2.750   0.5937   0.03355   0.02200  -0.0726   0.6299   1.0000
   3.000   0.5976   0.03437   0.02276  -0.0691   0.6173   1.0000
   3.250   0.6327   0.03394   0.02222  -0.0696   0.6124   1.0000
   3.500   0.6355   0.03492   0.02316  -0.0662   0.6000   1.0000
   3.750   0.6714   0.03445   0.02259  -0.0668   0.5956   1.0000
   4.000   0.6741   0.03557   0.02367  -0.0635   0.5835   1.0000
   4.250   0.7097   0.03510   0.02312  -0.0640   0.5793   1.0000
   4.500   0.7123   0.03638   0.02438  -0.0610   0.5679   1.0000
   4.750   0.7459   0.03604   0.02396  -0.0612   0.5635   1.0000
   5.000   0.7505   0.03735   0.02526  -0.0586   0.5532   1.0000
   5.250   0.7801   0.03724   0.02510  -0.0585   0.5480   1.0000
   5.750   0.8112   0.03883   0.02665  -0.0556   0.5332   1.0000
   6.000   0.8459   0.03850   0.02629  -0.0561   0.5296   1.0000
   6.250   0.8409   0.04072   0.02855  -0.0530   0.5195   1.0000
   6.500   0.8676   0.04087   0.02869  -0.0527   0.5146   1.0000
   6.750   0.9061   0.04033   0.02812  -0.0534   0.5116   1.0000
   7.000   0.8850   0.04384   0.03172  -0.0494   0.5002   1.0000
   7.250   0.9141   0.04390   0.03179  -0.0492   0.4964   1.0000
   7.500   0.9530   0.04333   0.03121  -0.0499   0.4939   1.0000
   7.750   0.9165   0.04835   0.03634  -0.0454   0.4812   1.0000
   8.000   0.9492   0.04806   0.03607  -0.0455   0.4781   1.0000
   8.500   0.9351   0.05447   0.04263  -0.0416   0.4620   1.0000
   8.750   0.9697   0.05389   0.04209  -0.0416   0.4597   1.0000
   9.250   0.9491   0.06148   0.04984  -0.0384   0.4428   1.0000
   9.750   0.9476   0.06705   0.05553  -0.0361   0.4257   1.0000
  10.000   0.9954   0.06414   0.05267  -0.0353   0.4231   1.0000
  10.500   1.0060   0.06771   0.05636  -0.0329   0.4055   1.0000
  11.000   1.0065   0.07287   0.06168  -0.0308   0.3881   1.0000
  11.500   1.0161   0.07701   0.06600  -0.0291   0.3718   1.0000
  12.000   1.0219   0.08161   0.07077  -0.0276   0.3545   1.0000
  12.500   0.9729   0.09405   0.08339  -0.0280   0.3259   1.0000
  12.750   1.0034   0.09244   0.08187  -0.0266   0.3222   1.0000
  13.250   1.0042   0.09808   0.08768  -0.0261   0.3028   1.0000
  13.750   0.9807   0.10778   0.09753  -0.0272   0.2780   1.0000
  14.000   1.0046   0.10706   0.09690  -0.0261   0.2739   1.0000
  14.500   1.0092   0.11281   0.10279  -0.0264   0.2580   1.0000
  14.750   0.9862   0.12025   0.11027  -0.0284   0.2457   1.0000
  15.000   1.0095   0.11955   0.10967  -0.0274   0.2427   1.0000
  15.500   1.0000   0.12866   0.11891  -0.0297   0.2285   1.0000
  16.000   0.9866   0.13897   0.12933  -0.0331   0.2154   1.0000
  16.250   1.0070   0.13881   0.12927  -0.0323   0.2131   1.0000
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