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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.85 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe174-il-1000000.txt
Download as CSV file: xf-goe174-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2281   0.09893   0.09744  -0.0284   1.0000   0.0121
  -9.500  -0.2246   0.09624   0.09476  -0.0284   1.0000   0.0123
  -9.250  -0.3136   0.10322   0.10162  -0.0249   1.0000   0.0120
  -9.000  -0.3080   0.10075   0.09916  -0.0249   1.0000   0.0121
  -8.750  -0.3031   0.09837   0.09680  -0.0250   1.0000   0.0122
  -8.500  -0.2993   0.09601   0.09445  -0.0251   1.0000   0.0124
  -8.250  -0.2966   0.09367   0.09214  -0.0250   1.0000   0.0126
  -8.000  -0.2957   0.09141   0.08991  -0.0247   1.0000   0.0128
  -7.750  -0.2902   0.08869   0.08721  -0.0258   0.9992   0.0132
  -7.500  -0.1577   0.06239   0.06092  -0.0528   0.9455   0.0150
  -6.000  -0.1110   0.05657   0.05454  -0.0760   0.8514   0.0166
  -5.250  -0.0159   0.03747   0.03488  -0.0986   0.8089   0.0192
  -5.000   0.0073   0.03610   0.03342  -0.0995   0.7929   0.0195
  -4.750   0.0328   0.03414   0.03133  -0.1010   0.7750   0.0201
  -4.500   0.0718   0.02761   0.02430  -0.1049   0.7574   0.0232
  -4.250   0.0970   0.02055   0.01655  -0.1074   0.7356   0.0239
  -4.000   0.1214   0.01968   0.01554  -0.1074   0.7001   0.0243
  -3.750   0.1466   0.01892   0.01458  -0.1074   0.6695   0.0250
  -3.500   0.1731   0.01802   0.01346  -0.1074   0.6499   0.0262
  -3.250   0.2026   0.01861   0.01373  -0.1069   0.6364   0.0289
  -3.000   0.2295   0.01505   0.00965  -0.1074   0.6270   0.0298
  -2.750   0.2565   0.01400   0.00854  -0.1075   0.6176   0.0307
  -2.500   0.2841   0.01337   0.00782  -0.1076   0.6093   0.0317
  -2.250   0.3119   0.01286   0.00718  -0.1075   0.6008   0.0333
  -2.000   0.3405   0.01374   0.00799  -0.1072   0.5933   0.0362
  -1.750   0.3679   0.01161   0.00565  -0.1075   0.5864   0.0392
  -1.500   0.3959   0.01120   0.00519  -0.1075   0.5795   0.0413
  -1.250   0.4249   0.01046   0.00427  -0.1071   0.5718   0.0346
  -1.000   0.4530   0.00972   0.00340  -0.1069   0.5642   0.0320
  -0.750   0.4810   0.00941   0.00304  -0.1068   0.5552   0.0323
  -0.500   0.5090   0.00909   0.00267  -0.1067   0.5447   0.0321
  -0.250   0.5368   0.00888   0.00240  -0.1066   0.5325   0.0324
   0.000   0.5646   0.00874   0.00220  -0.1064   0.5190   0.0329
   0.250   0.5923   0.00864   0.00204  -0.1063   0.5053   0.0333
   0.500   0.6200   0.00857   0.00191  -0.1062   0.4904   0.0337
   0.750   0.6476   0.00855   0.00181  -0.1061   0.4736   0.0340
   1.000   0.6751   0.00856   0.00175  -0.1060   0.4559   0.0348
   1.250   0.7024   0.00861   0.00171  -0.1058   0.4374   0.0355
   1.500   0.7295   0.00869   0.00170  -0.1056   0.4190   0.0360
   1.750   0.7566   0.00878   0.00169  -0.1054   0.4016   0.0375
   2.000   0.7837   0.00888   0.00171  -0.1052   0.3860   0.0403
   2.250   0.8108   0.00899   0.00177  -0.1051   0.3719   0.0449
   2.500   0.8380   0.00886   0.00193  -0.1051   0.3595   0.2117
   2.750   0.8613   0.00747   0.00221  -0.1046   0.3473   1.0000
   3.000   0.8883   0.00765   0.00230  -0.1045   0.3364   1.0000
   3.250   0.9153   0.00783   0.00241  -0.1043   0.3281   1.0000
   3.500   0.9426   0.00795   0.00251  -0.1042   0.3222   1.0000
   3.750   0.9696   0.00812   0.00263  -0.1040   0.3149   1.0000
   4.000   0.9967   0.00827   0.00274  -0.1039   0.3086   1.0000
   4.250   1.0237   0.00841   0.00286  -0.1037   0.3026   1.0000
   4.500   1.0504   0.00859   0.00301  -0.1036   0.2966   1.0000
   4.750   1.0776   0.00872   0.00313  -0.1035   0.2916   1.0000
   5.000   1.1042   0.00889   0.00328  -0.1033   0.2854   1.0000
   5.250   1.1310   0.00905   0.00343  -0.1031   0.2804   1.0000
   5.500   1.1578   0.00920   0.00358  -0.1030   0.2739   1.0000
   5.750   1.1840   0.00941   0.00375  -0.1027   0.2639   1.0000
   6.000   1.2098   0.00964   0.00393  -0.1025   0.2529   1.0000
   6.250   1.2358   0.00985   0.00412  -0.1022   0.2420   1.0000
   6.500   1.2609   0.01016   0.00434  -0.1019   0.2256   1.0000
   6.750   1.2856   0.01050   0.00460  -0.1014   0.2076   1.0000
   7.000   1.3075   0.01111   0.00501  -0.1006   0.1721   1.0000
   7.250   1.3262   0.01205   0.00567  -0.0993   0.1279   1.0000
   7.500   1.3489   0.01256   0.00611  -0.0986   0.1133   1.0000
   7.750   1.3721   0.01300   0.00650  -0.0980   0.1024   1.0000
   8.000   1.3893   0.01403   0.00726  -0.0965   0.0579   1.0000
   8.250   1.4110   0.01457   0.00780  -0.0956   0.0484   1.0000
   8.500   1.4322   0.01515   0.00838  -0.0947   0.0393   1.0000
   8.750   1.4501   0.01602   0.00909  -0.0932   0.0197   1.0000
   9.000   1.4702   0.01663   0.00972  -0.0921   0.0159   1.0000
   9.250   1.4891   0.01734   0.01047  -0.0908   0.0138   1.0000
   9.500   1.5093   0.01787   0.01106  -0.0897   0.0131   1.0000
   9.750   1.5284   0.01847   0.01172  -0.0884   0.0123   1.0000
  10.000   1.5459   0.01915   0.01245  -0.0870   0.0114   1.0000
  10.250   1.5595   0.02009   0.01347  -0.0849   0.0106   1.0000
  10.500   1.5715   0.02104   0.01452  -0.0827   0.0101   1.0000
  10.750   1.5848   0.02171   0.01526  -0.0805   0.0098   1.0000
  11.000   1.5952   0.02250   0.01612  -0.0780   0.0095   1.0000
  11.250   1.6042   0.02340   0.01710  -0.0754   0.0092   1.0000
  11.500   1.6119   0.02443   0.01820  -0.0728   0.0088   1.0000
  11.750   1.6183   0.02560   0.01945  -0.0704   0.0086   1.0000
  12.000   1.6230   0.02698   0.02092  -0.0680   0.0083   1.0000
  12.250   1.6249   0.02872   0.02275  -0.0658   0.0081   1.0000
  12.500   1.6213   0.03112   0.02526  -0.0637   0.0078   1.0000
  12.750   1.6100   0.03452   0.02881  -0.0619   0.0076   1.0000
  13.000   1.6009   0.03804   0.03247  -0.0607   0.0074   1.0000
  13.250   1.6055   0.04029   0.03481  -0.0603   0.0073   1.0000
  13.500   1.6066   0.04305   0.03767  -0.0601   0.0072   1.0000
  13.750   1.6053   0.04626   0.04098  -0.0601   0.0071   1.0000
  14.000   1.6016   0.04990   0.04474  -0.0604   0.0070   1.0000
  14.250   1.5956   0.05389   0.04884  -0.0609   0.0069   1.0000
  14.500   1.5877   0.05815   0.05322  -0.0614   0.0068   1.0000
  14.750   1.5785   0.06264   0.05782  -0.0620   0.0067   1.0000
  15.000   1.5684   0.06731   0.06259  -0.0627   0.0066   1.0000
  15.250   1.5583   0.07214   0.06753  -0.0636   0.0065   1.0000
  15.500   1.5481   0.07705   0.07255  -0.0647   0.0064   1.0000
  15.750   1.5376   0.08210   0.07769  -0.0658   0.0064   1.0000
  16.000   1.5270   0.08724   0.08294  -0.0670   0.0063   1.0000
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