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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 100,000
Max Cl/Cd: 53.23 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe174-il-100000.txt
Download as CSV file: xf-goe174-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2897   0.09638   0.09184  -0.0259   1.0000   0.0674
  -7.250  -0.2978   0.09566   0.09126  -0.0278   1.0000   0.0689
  -7.000  -0.3018   0.09525   0.09095  -0.0334   1.0000   0.0696
  -6.750  -0.3018   0.09378   0.08956  -0.0374   1.0000   0.0700
  -6.500  -0.3021   0.08775   0.08362  -0.0279   1.0000   0.0716
  -6.250  -0.3024   0.08525   0.08119  -0.0242   1.0000   0.0734
  -6.000  -0.3054   0.08342   0.07943  -0.0223   1.0000   0.0756
  -5.750  -0.3084   0.08171   0.07778  -0.0217   1.0000   0.0784
  -5.500  -0.3072   0.08027   0.07637  -0.0248   1.0000   0.0823
  -5.250  -0.2925   0.07770   0.07375  -0.0341   0.9991   0.0850
  -5.000  -0.2739   0.07306   0.06918  -0.0318   0.9938   0.0887
  -4.750  -0.2065   0.06762   0.06347  -0.0507   0.9843   0.1004
  -4.500  -0.1831   0.06355   0.05947  -0.0504   0.9759   0.1050
  -4.250  -0.1318   0.05887   0.05460  -0.0612   0.9661   0.1175
  -4.000  -0.0842   0.05477   0.05039  -0.0690   0.9586   0.1328
  -3.750  -0.0395   0.05102   0.04651  -0.0756   0.9480   0.1475
  -3.500   0.0045   0.04750   0.04287  -0.0813   0.9375   0.1633
  -3.000   0.1105   0.04096   0.03588  -0.0954   0.9201   0.2190
  -2.750   0.1485   0.03750   0.03243  -0.0980   0.9097   0.2378
  -2.250   0.2793   0.01146   0.00491  -0.1092   0.8613   0.1309
  -2.000   0.3182   0.02461   0.01718  -0.1149   0.8801   0.1104
  -1.750   0.3594   0.02267   0.01449  -0.1160   0.8681   0.0991
  -1.500   0.3941   0.02102   0.01258  -0.1166   0.8550   0.0970
  -1.250   0.4259   0.02000   0.01130  -0.1165   0.8407   0.0973
  -1.000   0.4555   0.01936   0.01040  -0.1160   0.8257   0.0993
  -0.750   0.4833   0.01854   0.00949  -0.1153   0.8106   0.1002
  -0.500   0.5101   0.01788   0.00880  -0.1145   0.7955   0.1023
  -0.250   0.5366   0.01741   0.00831  -0.1136   0.7804   0.1061
   0.000   0.5627   0.01708   0.00789  -0.1125   0.7653   0.1123
   0.250   0.5893   0.01675   0.00754  -0.1117   0.7501   0.1267
   0.500   0.6167   0.01618   0.00739  -0.1111   0.7349   0.2501
   0.750   0.6432   0.01454   0.00711  -0.1099   0.7198   1.0000
   1.000   0.6698   0.01469   0.00696  -0.1091   0.7040   1.0000
   1.250   0.6958   0.01487   0.00691  -0.1083   0.6873   1.0000
   1.500   0.7218   0.01509   0.00690  -0.1075   0.6703   1.0000
   1.750   0.7479   0.01535   0.00696  -0.1068   0.6533   1.0000
   2.000   0.7739   0.01567   0.00709  -0.1061   0.6365   1.0000
   2.250   0.7997   0.01603   0.00727  -0.1054   0.6196   1.0000
   2.500   0.8255   0.01641   0.00749  -0.1048   0.6030   1.0000
   2.750   0.8511   0.01681   0.00775  -0.1041   0.5868   1.0000
   3.000   0.8767   0.01721   0.00805  -0.1035   0.5715   1.0000
   3.250   0.9022   0.01762   0.00838  -0.1030   0.5572   1.0000
   3.500   0.9277   0.01803   0.00871  -0.1025   0.5438   1.0000
   3.750   0.9534   0.01842   0.00905  -0.1020   0.5315   1.0000
   4.000   0.9799   0.01879   0.00930  -0.1015   0.5209   1.0000
   4.250   1.0049   0.01921   0.00975  -0.1010   0.5095   1.0000
   4.500   1.0301   0.01967   0.01021  -0.1006   0.4991   1.0000
   4.750   1.0565   0.02005   0.01054  -0.1002   0.4901   1.0000
   5.000   1.0813   0.02047   0.01100  -0.0997   0.4798   1.0000
   5.250   1.1062   0.02094   0.01150  -0.0992   0.4703   1.0000
   5.500   1.1327   0.02133   0.01182  -0.0988   0.4623   1.0000
   5.750   1.1564   0.02185   0.01250  -0.0982   0.4526   1.0000
   6.000   1.1823   0.02230   0.01292  -0.0978   0.4447   1.0000
   6.250   1.2062   0.02284   0.01357  -0.0973   0.4360   1.0000
   6.500   1.2310   0.02337   0.01417  -0.0968   0.4279   1.0000
   6.750   1.2557   0.02379   0.01463  -0.0962   0.4190   1.0000
   7.000   1.2785   0.02436   0.01533  -0.0954   0.4096   1.0000
   7.250   1.3043   0.02475   0.01567  -0.0950   0.4009   1.0000
   7.500   1.3259   0.02528   0.01641  -0.0941   0.3910   1.0000
   7.750   1.3492   0.02587   0.01711  -0.0934   0.3825   1.0000
   8.000   1.3733   0.02639   0.01771  -0.0928   0.3743   1.0000
   8.250   1.3946   0.02711   0.01864  -0.0918   0.3658   1.0000
   8.500   1.4187   0.02746   0.01901  -0.0912   0.3556   1.0000
   8.750   1.4401   0.02760   0.01916  -0.0900   0.3420   1.0000
   9.000   1.4579   0.02769   0.01935  -0.0883   0.3268   1.0000
   9.250   1.4732   0.02780   0.01960  -0.0862   0.3110   1.0000
   9.500   1.4870   0.02795   0.01997  -0.0840   0.2951   1.0000
   9.750   1.4995   0.02817   0.02043  -0.0816   0.2787   1.0000
  10.000   1.5079   0.02834   0.02083  -0.0786   0.2564   1.0000
  10.250   1.5086   0.02883   0.02140  -0.0746   0.2110   1.0000
  10.500   1.4905   0.03122   0.02320  -0.0689   0.1354   1.0000
  10.750   1.4710   0.03443   0.02608  -0.0639   0.0969   1.0000
  11.000   1.4560   0.03765   0.02914  -0.0604   0.0762   1.0000
  11.250   1.4415   0.04115   0.03259  -0.0579   0.0694   1.0000
  11.500   1.4280   0.04493   0.03649  -0.0564   0.0653   1.0000
  11.750   1.4127   0.04924   0.04090  -0.0556   0.0625   1.0000
  12.000   1.3962   0.05405   0.04580  -0.0555   0.0605   1.0000
  12.250   1.3838   0.05860   0.05048  -0.0555   0.0585   1.0000
  12.500   1.3747   0.06283   0.05486  -0.0555   0.0564   1.0000
  12.750   1.3675   0.06668   0.05881  -0.0552   0.0545   1.0000
  13.000   1.3646   0.06975   0.06193  -0.0542   0.0524   1.0000
  13.250   1.3875   0.06872   0.06054  -0.0480   0.0487   1.0000
  13.500   1.3935   0.07119   0.06322  -0.0471   0.0473   1.0000
  13.750   1.3991   0.07378   0.06600  -0.0461   0.0455   1.0000
  14.000   1.4067   0.07623   0.06859  -0.0449   0.0436   1.0000
  14.250   1.4172   0.07859   0.07108  -0.0434   0.0423   1.0000
  14.500   1.4264   0.08133   0.07400  -0.0421   0.0415   1.0000
  14.750   1.4315   0.08466   0.07752  -0.0413   0.0409   1.0000
  15.000   1.4311   0.08861   0.08169  -0.0411   0.0406   1.0000
  15.250   1.4249   0.09314   0.08647  -0.0416   0.0406   1.0000
  15.500   1.4142   0.09815   0.09174  -0.0428   0.0406   1.0000
  15.750   1.4002   0.10366   0.09751  -0.0446   0.0407   1.0000
  16.000   1.3835   0.10974   0.10386  -0.0472   0.0409   1.0000
  16.250   1.3614   0.11695   0.11135  -0.0512   0.0413   1.0000
  16.500   1.3324   0.12597   0.12069  -0.0571   0.0420   1.0000
  16.750   1.3027   0.13612   0.13113  -0.0642   0.0428   1.0000
  17.000   1.2714   0.14773   0.14298  -0.0725   0.0438   1.0000
  17.250   1.2362   0.16161   0.15704  -0.0826   0.0450   1.0000
  17.500   1.2015   0.17712   0.17264  -0.0933   0.0467   1.0000
  17.750   1.1839   0.18870   0.18420  -0.1002   0.0481   1.0000
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