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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 500,000
Max Cl/Cd: 104.36 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe174-il-500000.txt
Download as CSV file: xf-goe174-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2957   0.10140   0.09918  -0.0261   1.0000   0.0185
  -8.500  -0.2976   0.09891   0.09672  -0.0276   1.0000   0.0186
  -8.250  -0.3003   0.09640   0.09426  -0.0281   1.0000   0.0186
  -8.000  -0.2238   0.08010   0.07820  -0.0301   0.9993   0.0190
  -7.750  -0.2072   0.07610   0.07420  -0.0322   0.9970   0.0193
  -7.500  -0.1918   0.07204   0.07014  -0.0355   0.9939   0.0198
  -7.250  -0.1780   0.06794   0.06604  -0.0392   0.9878   0.0203
  -7.000  -0.1654   0.06376   0.06186  -0.0431   0.9774   0.0211
  -6.750  -0.1515   0.05924   0.05733  -0.0480   0.9623   0.0220
  -6.000  -0.1320   0.05943   0.05724  -0.0732   0.9565   0.0232
  -5.750  -0.1013   0.05291   0.05064  -0.0806   0.9438   0.0236
  -5.500  -0.0685   0.04989   0.04756  -0.0849   0.9286   0.0242
  -5.250  -0.0324   0.04653   0.04405  -0.0904   0.9075   0.0251
  -5.000   0.0001   0.04283   0.04015  -0.0952   0.8852   0.0267
  -4.750   0.0465   0.03306   0.02982  -0.1049   0.8686   0.0295
  -4.500   0.0678   0.03179   0.02847  -0.1051   0.8510   0.0302
  -4.250   0.0918   0.03022   0.02677  -0.1057   0.8346   0.0311
  -4.000   0.1188   0.02784   0.02416  -0.1067   0.8182   0.0329
  -3.750   0.1515   0.02275   0.01832  -0.1087   0.8028   0.0374
  -3.500   0.1756   0.02164   0.01719  -0.1087   0.7836   0.0387
  -3.250   0.2014   0.02057   0.01592  -0.1087   0.7633   0.0411
  -3.000   0.2299   0.01864   0.01342  -0.1089   0.7403   0.0473
  -2.750   0.2551   0.01768   0.01239  -0.1087   0.7146   0.0495
  -2.500   0.2817   0.01720   0.01165  -0.1084   0.6908   0.0542
  -2.250   0.3079   0.01615   0.01037  -0.1085   0.6727   0.0615
  -2.000   0.3361   0.01790   0.01192  -0.1077   0.6573   0.0699
  -1.750   0.3615   0.01513   0.00905  -0.1083   0.6454   0.0786
  -1.500   0.3885   0.01451   0.00830  -0.1084   0.6341   0.0912
  -1.250   0.4200   0.01419   0.00751  -0.1073   0.6243   0.0698
  -1.000   0.4497   0.01165   0.00456  -0.1066   0.6156   0.0442
  -0.750   0.4775   0.01106   0.00390  -0.1064   0.6069   0.0430
  -0.250   0.5327   0.01042   0.00313  -0.1059   0.5889   0.0426
   0.000   0.5603   0.01022   0.00288  -0.1057   0.5798   0.0429
   0.250   0.5879   0.01007   0.00268  -0.1056   0.5697   0.0433
   0.500   0.6156   0.00995   0.00254  -0.1054   0.5588   0.0445
   0.750   0.6432   0.00988   0.00241  -0.1052   0.5471   0.0453
   1.000   0.6706   0.00983   0.00230  -0.1050   0.5342   0.0459
   1.250   0.6980   0.00979   0.00220  -0.1048   0.5203   0.0481
   1.500   0.7253   0.00980   0.00215  -0.1046   0.5045   0.0527
   1.750   0.7524   0.00961   0.00223  -0.1045   0.4867   0.1855
   2.000   0.7791   0.00951   0.00232  -0.1044   0.4679   0.2891
   2.250   0.8024   0.00823   0.00248  -0.1037   0.4500   1.0000
   2.500   0.8288   0.00845   0.00256  -0.1033   0.4321   1.0000
   2.750   0.8552   0.00867   0.00266  -0.1030   0.4156   1.0000
   3.000   0.8815   0.00890   0.00278  -0.1027   0.4004   1.0000
   3.250   0.9076   0.00914   0.00292  -0.1024   0.3865   1.0000
   3.500   0.9340   0.00936   0.00306  -0.1022   0.3744   1.0000
   3.750   0.9604   0.00958   0.00322  -0.1019   0.3636   1.0000
   4.000   0.9865   0.00981   0.00339  -0.1016   0.3542   1.0000
   4.250   1.0128   0.01003   0.00356  -0.1013   0.3458   1.0000
   4.500   1.0391   0.01024   0.00374  -0.1011   0.3382   1.0000
   4.750   1.0653   0.01045   0.00394  -0.1008   0.3312   1.0000
   5.000   1.0913   0.01068   0.00415  -0.1005   0.3249   1.0000
   5.250   1.1176   0.01087   0.00434  -0.1003   0.3182   1.0000
   5.500   1.1430   0.01115   0.00459  -0.0999   0.3124   1.0000
   5.750   1.1696   0.01131   0.00479  -0.0997   0.3074   1.0000
   6.000   1.1954   0.01153   0.00502  -0.0994   0.3016   1.0000
   6.250   1.2210   0.01176   0.00524  -0.0991   0.2939   1.0000
   6.500   1.2464   0.01198   0.00548  -0.0987   0.2851   1.0000
   6.750   1.2721   0.01219   0.00570  -0.0984   0.2766   1.0000
   7.000   1.2970   0.01246   0.00595  -0.0980   0.2663   1.0000
   7.250   1.3220   0.01271   0.00621  -0.0976   0.2551   1.0000
   7.500   1.3468   0.01298   0.00648  -0.0972   0.2432   1.0000
   7.750   1.3709   0.01330   0.00679  -0.0967   0.2288   1.0000
   8.000   1.3934   0.01377   0.00716  -0.0960   0.2054   1.0000
   8.250   1.4106   0.01475   0.00784  -0.0946   0.1561   1.0000
   8.500   1.4268   0.01580   0.00868  -0.0931   0.1227   1.0000
   8.750   1.4441   0.01671   0.00948  -0.0916   0.0985   1.0000
   9.000   1.4535   0.01830   0.01076  -0.0891   0.0508   1.0000
   9.250   1.4691   0.01926   0.01174  -0.0873   0.0345   1.0000
   9.500   1.4828   0.02032   0.01272  -0.0853   0.0229   1.0000
   9.750   1.4977   0.02120   0.01364  -0.0835   0.0201   1.0000
  10.000   1.5085   0.02231   0.01483  -0.0810   0.0180   1.0000
  10.250   1.5194   0.02319   0.01582  -0.0785   0.0173   1.0000
  10.500   1.5274   0.02421   0.01694  -0.0757   0.0165   1.0000
  10.750   1.5337   0.02537   0.01821  -0.0729   0.0158   1.0000
  11.000   1.5377   0.02674   0.01969  -0.0700   0.0151   1.0000
  11.250   1.5369   0.02856   0.02161  -0.0671   0.0144   1.0000
  11.500   1.5304   0.03105   0.02424  -0.0643   0.0139   1.0000
  11.750   1.5249   0.03374   0.02708  -0.0623   0.0136   1.0000
  12.000   1.5264   0.03602   0.02949  -0.0611   0.0133   1.0000
  12.250   1.5252   0.03872   0.03231  -0.0602   0.0131   1.0000
  12.500   1.5225   0.04179   0.03550  -0.0596   0.0128   1.0000
  12.750   1.5182   0.04521   0.03905  -0.0593   0.0126   1.0000
  13.000   1.5132   0.04891   0.04289  -0.0594   0.0124   1.0000
  13.250   1.5073   0.05281   0.04690  -0.0596   0.0122   1.0000
  13.500   1.5007   0.05683   0.05104  -0.0599   0.0120   1.0000
  13.750   1.4935   0.06094   0.05527  -0.0602   0.0118   1.0000
  14.000   1.4860   0.06510   0.05954  -0.0606   0.0117   1.0000
  14.250   1.4786   0.06930   0.06383  -0.0610   0.0115   1.0000
  14.500   1.4717   0.07352   0.06814  -0.0615   0.0114   1.0000
  14.750   1.4651   0.07770   0.07242  -0.0620   0.0112   1.0000
  15.000   1.4592   0.08182   0.07661  -0.0626   0.0110   1.0000
  15.250   1.4539   0.08582   0.08068  -0.0630   0.0108   1.0000
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