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GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 328 AIRFOIL (goe328-il)
Reynolds number: 100,000
Max Cl/Cd: 56.91 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe328-il-100000.txt
Download as CSV file: xf-goe328-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 328 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3495   0.09759   0.09270  -0.0214   1.0000   0.0694
  -7.500  -0.3498   0.09565   0.09084  -0.0244   1.0000   0.0712
  -7.250  -0.3465   0.09450   0.08973  -0.0341   1.0000   0.0724
  -7.000  -0.3390   0.09303   0.08822  -0.0423   1.0000   0.0729
  -6.750  -0.3350   0.08662   0.08196  -0.0364   1.0000   0.0739
  -6.500  -0.3298   0.08302   0.07843  -0.0326   1.0000   0.0753
  -6.250  -0.3270   0.08045   0.07592  -0.0308   1.0000   0.0769
  -6.000  -0.3277   0.07838   0.07392  -0.0297   1.0000   0.0789
  -5.750  -0.3308   0.07658   0.07217  -0.0287   1.0000   0.0811
  -5.500  -0.3328   0.07487   0.07047  -0.0289   1.0000   0.0837
  -5.250  -0.3161   0.07563   0.07085  -0.0398   1.0000   0.0875
  -5.000  -0.3193   0.07069   0.06610  -0.0360   1.0000   0.0884
  -4.750  -0.3193   0.06775   0.06326  -0.0331   1.0000   0.0895
  -4.500  -0.3116   0.06517   0.06071  -0.0321   0.9992   0.0916
  -4.250  -0.2665   0.06127   0.05665  -0.0402   0.9927   0.0990
  -4.000  -0.2174   0.05653   0.05169  -0.0495   0.9851   0.1052
  -3.500  -0.1269   0.04917   0.04404  -0.0625   0.9704   0.1250
  -3.250  -0.0859   0.04600   0.04068  -0.0679   0.9613   0.1374
  -3.000  -0.0397   0.04291   0.03742  -0.0738   0.9561   0.1529
  -2.750  -0.0001   0.04116   0.03541  -0.0779   0.9469   0.1763
  -2.500   0.0413   0.03778   0.03203  -0.0824   0.9419   0.1979
  -2.250   0.0755   0.03562   0.02982  -0.0850   0.9333   0.2299
  -1.750   0.1402   0.03130   0.02564  -0.0883   0.9184   0.3500
  -1.500   0.1728   0.02907   0.02351  -0.0890   0.9115   0.4118
  -1.250   0.2020   0.02717   0.02165  -0.0891   0.9012   0.4484
  -1.000   0.3056   0.02562   0.01773  -0.1005   0.8954   0.1494
  -0.750   0.3411   0.02460   0.01615  -0.0999   0.8841   0.1164
  -0.500   0.3735   0.02297   0.01442  -0.1001   0.8741   0.1095
  -0.250   0.4057   0.02198   0.01323  -0.0999   0.8642   0.1083
   0.000   0.4334   0.02124   0.01235  -0.0990   0.8513   0.1076
   0.250   0.4611   0.02056   0.01151  -0.0980   0.8387   0.1053
   0.500   0.4880   0.01989   0.01079  -0.0968   0.8259   0.1052
   0.750   0.5141   0.01922   0.01012  -0.0955   0.8126   0.1067
   1.000   0.5393   0.01862   0.00954  -0.0939   0.7984   0.1099
   1.250   0.5640   0.01822   0.00907  -0.0923   0.7831   0.1171
   1.500   0.5891   0.01773   0.00858  -0.0909   0.7673   0.1289
   1.750   0.6153   0.01736   0.00816  -0.0897   0.7512   0.1478
   2.000   0.6383   0.01518   0.00775  -0.0875   0.7360   1.0000
   2.250   0.6642   0.01526   0.00754  -0.0864   0.7189   1.0000
   2.500   0.6900   0.01536   0.00745  -0.0854   0.7016   1.0000
   2.750   0.7160   0.01548   0.00742  -0.0845   0.6843   1.0000
   3.000   0.7421   0.01563   0.00743  -0.0837   0.6672   1.0000
   3.250   0.7683   0.01581   0.00748  -0.0830   0.6504   1.0000
   3.500   0.7946   0.01602   0.00756  -0.0823   0.6338   1.0000
   3.750   0.8207   0.01627   0.00774  -0.0817   0.6167   1.0000
   4.000   0.8467   0.01655   0.00796  -0.0812   0.5995   1.0000
   4.250   0.8728   0.01684   0.00819  -0.0807   0.5829   1.0000
   4.500   0.8989   0.01715   0.00845  -0.0802   0.5672   1.0000
   4.750   0.9251   0.01749   0.00877  -0.0798   0.5523   1.0000
   5.000   0.9514   0.01786   0.00910  -0.0794   0.5381   1.0000
   5.250   0.9777   0.01825   0.00947  -0.0790   0.5248   1.0000
   5.500   1.0042   0.01868   0.00988  -0.0786   0.5124   1.0000
   5.750   1.0300   0.01918   0.01043  -0.0783   0.4994   1.0000
   6.000   1.0557   0.01973   0.01104  -0.0780   0.4872   1.0000
   6.250   1.0817   0.02032   0.01168  -0.0777   0.4763   1.0000
   6.500   1.1074   0.02082   0.01220  -0.0773   0.4644   1.0000
   6.750   1.1322   0.02122   0.01261  -0.0766   0.4498   1.0000
   7.000   1.1557   0.02155   0.01298  -0.0758   0.4326   1.0000
   7.250   1.1783   0.02175   0.01324  -0.0747   0.4130   1.0000
   7.500   1.2005   0.02188   0.01334  -0.0736   0.3927   1.0000
   7.750   1.2205   0.02197   0.01358  -0.0722   0.3697   1.0000
   8.000   1.2395   0.02199   0.01371  -0.0707   0.3435   1.0000
   8.250   1.2531   0.02202   0.01384  -0.0683   0.2883   1.0000
   8.500   1.2450   0.02514   0.01562  -0.0641   0.1158   1.0000
   8.750   1.2466   0.02784   0.01811  -0.0609   0.0915   1.0000
   9.000   1.2502   0.02996   0.02024  -0.0580   0.0818   1.0000
   9.250   1.2574   0.03163   0.02203  -0.0554   0.0750   1.0000
   9.500   1.2580   0.03362   0.02397  -0.0523   0.0704   1.0000
   9.750   1.2636   0.03538   0.02580  -0.0495   0.0669   1.0000
  10.000   1.2745   0.03712   0.02758  -0.0473   0.0639   1.0000
  10.250   1.2917   0.03900   0.02941  -0.0458   0.0609   1.0000
  10.500   1.3274   0.04181   0.03208  -0.0466   0.0571   1.0000
  10.750   1.3488   0.04386   0.03436  -0.0457   0.0549   1.0000
  11.000   1.3750   0.04651   0.03721  -0.0454   0.0536   1.0000
  11.250   1.3965   0.04945   0.04042  -0.0446   0.0529   1.0000
  11.500   1.4102   0.05245   0.04374  -0.0432   0.0522   1.0000
  11.750   1.4193   0.05539   0.04695  -0.0415   0.0512   1.0000
  12.000   1.4284   0.05846   0.05022  -0.0400   0.0501   1.0000
  12.250   1.4326   0.06182   0.05383  -0.0382   0.0495   1.0000
  12.500   1.4192   0.06488   0.05728  -0.0345   0.0500   1.0000
  12.750   1.4002   0.06832   0.06112  -0.0314   0.0506   1.0000
  13.000   1.3794   0.07232   0.06547  -0.0293   0.0513   1.0000
  13.250   1.3579   0.07686   0.07035  -0.0282   0.0520   1.0000
  13.500   1.3351   0.08190   0.07569  -0.0282   0.0527   1.0000
  13.750   1.3111   0.08750   0.08154  -0.0291   0.0533   1.0000
  14.000   1.2859   0.09369   0.08798  -0.0310   0.0540   1.0000
  14.250   1.2599   0.10050   0.09500  -0.0339   0.0546   1.0000
  14.500   1.2332   0.10806   0.10275  -0.0378   0.0552   1.0000
  14.750   1.2067   0.11632   0.11117  -0.0426   0.0559   1.0000
  15.000   1.1830   0.12503   0.12000  -0.0476   0.0568   1.0000
  15.250   1.1859   0.13049   0.12551  -0.0481   0.0585   1.0000
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