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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 200,000
Max Cl/Cd: 72.26 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe613-il-200000.txt
Download as CSV file: xf-goe613-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3726   0.09189   0.08878  -0.0245   1.0000   0.0446
  -7.500  -0.3907   0.09057   0.08753  -0.0219   1.0000   0.0451
  -7.250  -0.4113   0.08943   0.08647  -0.0190   1.0000   0.0452
  -7.000  -0.3847   0.08223   0.07913  -0.0402   0.9905   0.0479
  -6.750  -0.3613   0.07427   0.07096  -0.0515   0.9840   0.0486
  -6.500  -0.3489   0.07040   0.06723  -0.0494   0.9801   0.0498
  -6.250  -0.3266   0.06746   0.06428  -0.0509   0.9752   0.0516
  -6.000  -0.2961   0.06315   0.05986  -0.0569   0.9714   0.0546
  -5.750  -0.2602   0.05873   0.05476  -0.0669   0.9604   0.0603
  -5.500  -0.2383   0.05165   0.04775  -0.0705   0.9579   0.0620
  -5.250  -0.2213   0.04932   0.04546  -0.0703   0.9496   0.0638
  -5.000  -0.1895   0.04650   0.04252  -0.0735   0.9460   0.0689
  -4.750  -0.1662   0.04250   0.03801  -0.0755   0.9381   0.0756
  -4.500  -0.1389   0.04004   0.03558  -0.0770   0.9339   0.0784
  -4.250  -0.1022   0.03747   0.03247  -0.0801   0.9306   0.0896
  -4.000  -0.0832   0.03526   0.03039  -0.0797   0.9236   0.0927
  -3.750  -0.0515   0.03331   0.02809  -0.0813   0.9190   0.1054
  -3.500  -0.0151   0.03137   0.02610  -0.0837   0.9166   0.1140
  -3.250   0.0234   0.02917   0.02375  -0.0866   0.9149   0.1277
  -3.000   0.0415   0.02779   0.02227  -0.0852   0.9052   0.1403
  -2.750   0.0833   0.02596   0.02030  -0.0885   0.9024   0.1687
  -2.250   0.1681   0.01996   0.01263  -0.0881   0.8909   0.0725
  -2.000   0.2091   0.01829   0.01079  -0.0901   0.8871   0.0710
  -1.750   0.2391   0.01749   0.00985  -0.0901   0.8795   0.0721
  -1.500   0.2742   0.01651   0.00878  -0.0909   0.8731   0.0725
  -1.250   0.3054   0.01568   0.00791  -0.0911   0.8655   0.0727
  -1.000   0.3372   0.01495   0.00714  -0.0913   0.8574   0.0736
  -0.750   0.3631   0.01419   0.00640  -0.0905   0.8473   0.0752
  -0.500   0.3942   0.01348   0.00574  -0.0908   0.8389   0.0791
  -0.250   0.4198   0.01310   0.00536  -0.0899   0.8272   0.0850
   0.000   0.4450   0.01271   0.00495  -0.0889   0.8147   0.0904
   0.250   0.4713   0.01236   0.00457  -0.0882   0.8019   0.1027
   0.500   0.5744   0.00973   0.00431  -0.1037   0.7904   1.0000
   0.750   0.5981   0.00970   0.00413  -0.1025   0.7738   1.0000
   1.000   0.6221   0.00971   0.00399  -0.1013   0.7562   1.0000
   1.250   0.6462   0.00975   0.00386  -0.1002   0.7373   1.0000
   1.500   0.6680   0.00984   0.00382  -0.0987   0.7161   1.0000
   1.750   0.6900   0.00995   0.00379  -0.0973   0.6940   1.0000
   2.000   0.7108   0.01008   0.00380  -0.0956   0.6701   1.0000
   2.250   0.7313   0.01024   0.00380  -0.0939   0.6443   1.0000
   2.500   0.7510   0.01042   0.00382  -0.0920   0.6163   1.0000
   2.750   0.7703   0.01066   0.00388  -0.0901   0.5876   1.0000
   3.000   0.7894   0.01095   0.00398  -0.0882   0.5608   1.0000
   3.250   0.8089   0.01129   0.00414  -0.0864   0.5369   1.0000
   3.500   0.8286   0.01166   0.00434  -0.0848   0.5150   1.0000
   3.750   0.8486   0.01203   0.00458  -0.0832   0.4947   1.0000
   4.000   0.8686   0.01237   0.00482  -0.0816   0.4748   1.0000
   4.250   0.8888   0.01271   0.00507  -0.0801   0.4566   1.0000
   4.500   0.9091   0.01305   0.00532  -0.0787   0.4399   1.0000
   4.750   0.9299   0.01340   0.00560  -0.0773   0.4249   1.0000
   5.000   0.9510   0.01374   0.00588  -0.0761   0.4113   1.0000
   5.250   0.9724   0.01409   0.00619  -0.0748   0.3988   1.0000
   5.500   0.9939   0.01447   0.00650  -0.0737   0.3875   1.0000
   5.750   1.0156   0.01487   0.00683  -0.0726   0.3769   1.0000
   6.000   1.0366   0.01519   0.00717  -0.0714   0.3655   1.0000
   6.250   1.0570   0.01554   0.00750  -0.0701   0.3536   1.0000
   6.500   1.0763   0.01588   0.00781  -0.0686   0.3410   1.0000
   6.750   1.0961   0.01625   0.00815  -0.0672   0.3299   1.0000
   7.000   1.1162   0.01658   0.00851  -0.0659   0.3201   1.0000
   7.250   1.1352   0.01690   0.00886  -0.0644   0.3091   1.0000
   7.500   1.1534   0.01724   0.00920  -0.0627   0.2981   1.0000
   7.750   1.1722   0.01759   0.00958  -0.0612   0.2889   1.0000
   8.000   1.1896   0.01787   0.00995  -0.0594   0.2778   1.0000
   8.250   1.2058   0.01817   0.01029  -0.0575   0.2657   1.0000
   8.500   1.2192   0.01845   0.01060  -0.0550   0.2507   1.0000
   8.750   1.2331   0.01879   0.01098  -0.0526   0.2373   1.0000
   9.000   1.2471   0.01918   0.01140  -0.0503   0.2233   1.0000
   9.250   1.2580   0.01969   0.01185  -0.0476   0.2010   1.0000
   9.500   1.2685   0.02038   0.01243  -0.0450   0.1667   1.0000
   9.750   1.2687   0.02182   0.01346  -0.0412   0.1146   1.0000
  10.000   1.2579   0.02415   0.01527  -0.0364   0.0489   1.0000
  10.250   1.2584   0.02577   0.01681  -0.0331   0.0352   1.0000
  10.500   1.2653   0.02698   0.01812  -0.0306   0.0320   1.0000
  10.750   1.2710   0.02830   0.01956  -0.0282   0.0300   1.0000
  11.000   1.2747   0.02980   0.02118  -0.0257   0.0286   1.0000
  11.250   1.2744   0.03162   0.02316  -0.0231   0.0273   1.0000
  11.500   1.2744   0.03350   0.02518  -0.0209   0.0266   1.0000
  11.750   1.2748   0.03544   0.02728  -0.0190   0.0261   1.0000
  12.000   1.2738   0.03760   0.02958  -0.0173   0.0254   1.0000
  12.250   1.2706   0.04009   0.03221  -0.0158   0.0248   1.0000
  12.500   1.2658   0.04289   0.03515  -0.0146   0.0244   1.0000
  12.750   1.2607   0.04588   0.03828  -0.0138   0.0241   1.0000
  13.000   1.2546   0.04914   0.04165  -0.0132   0.0239   1.0000
  13.250   1.2498   0.05240   0.04502  -0.0128   0.0237   1.0000
  13.500   1.2445   0.05586   0.04858  -0.0127   0.0234   1.0000
  13.750   1.2420   0.05908   0.05189  -0.0126   0.0233   1.0000
  14.000   1.2406   0.06222   0.05511  -0.0125   0.0232   1.0000
  14.250   1.2403   0.06522   0.05817  -0.0123   0.0229   1.0000
  14.500   1.2431   0.06786   0.06088  -0.0119   0.0227   1.0000
  14.750   1.2486   0.07012   0.06321  -0.0112   0.0227   1.0000
  15.000   1.2561   0.07219   0.06536  -0.0105   0.0225   1.0000
  15.250   1.2658   0.07404   0.06722  -0.0094   0.0220   1.0000
  15.500   1.2799   0.07561   0.06883  -0.0078   0.0215   1.0000
  15.750   1.2951   0.07773   0.07106  -0.0063   0.0212   1.0000
  16.000   1.2972   0.08088   0.07437  -0.0065   0.0213   1.0000
  16.250   1.2964   0.08439   0.07807  -0.0071   0.0214   1.0000
  16.500   1.2918   0.08831   0.08218  -0.0083   0.0216   1.0000
  16.750   1.2863   0.09268   0.08676  -0.0096   0.0217   1.0000
  17.000   1.2764   0.09764   0.09196  -0.0116   0.0219   1.0000
  17.250   1.2642   0.10328   0.09786  -0.0142   0.0223   1.0000
  17.500   1.2486   0.10977   0.10464  -0.0174   0.0228   1.0000
  17.750   1.2296   0.11711   0.11225  -0.0215   0.0231   1.0000
  18.000   1.2094   0.12503   0.12043  -0.0261   0.0235   1.0000
  18.250   1.1892   0.13329   0.12892  -0.0312   0.0239   1.0000
  18.500   1.1684   0.14209   0.13793  -0.0368   0.0244   1.0000
  18.750   1.1466   0.15153   0.14756  -0.0430   0.0247   1.0000
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