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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 100,000
Max Cl/Cd: 57.31 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe377-il-100000.txt
Download as CSV file: xf-goe377-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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  -0.3710   0.09445   0.08967  -0.0244   1.0000   0.0590
  -7.500  -0.3767   0.09266   0.08798  -0.0246   1.0000   0.0599
  -7.250  -0.3819   0.09121   0.08662  -0.0274   1.0000   0.0610
  -7.000  -0.3822   0.08975   0.08519  -0.0314   1.0000   0.0616
  -6.750  -0.3797   0.08815   0.08355  -0.0350   1.0000   0.0619
  -6.500  -0.3785   0.08272   0.07823  -0.0327   1.0000   0.0627
  -6.250  -0.3764   0.07847   0.07404  -0.0279   1.0000   0.0643
  -6.000  -0.3737   0.07562   0.07122  -0.0261   1.0000   0.0661
  -5.750  -0.3704   0.07293   0.06855  -0.0256   1.0000   0.0684
  -5.500  -0.3652   0.07027   0.06588  -0.0259   1.0000   0.0710
  -5.250  -0.3455   0.06910   0.06440  -0.0328   1.0000   0.0758
  -5.000  -0.3410   0.06454   0.05988  -0.0319   1.0000   0.0771
  -4.750  -0.3386   0.06102   0.05647  -0.0287   1.0000   0.0792
  -4.500  -0.3300   0.05839   0.05383  -0.0276   1.0000   0.0829
  -4.250  -0.3081   0.05565   0.05077  -0.0312   1.0000   0.0914
  -4.000  -0.3034   0.05262   0.04789  -0.0285   1.0000   0.0959
  -3.750  -0.2830   0.04993   0.04491  -0.0303   1.0000   0.1061
  -3.500  -0.2726   0.04724   0.04227  -0.0287   1.0000   0.1116
  -3.250  -0.2546   0.04458   0.03940  -0.0291   1.0000   0.1223
  -3.000  -0.2364   0.04235   0.03698  -0.0292   1.0000   0.1353
  -2.750  -0.2199   0.04012   0.03466  -0.0287   1.0000   0.1499
  -2.500  -0.2044   0.03810   0.03260  -0.0278   1.0000   0.1678
  -2.250  -0.1880   0.03656   0.03091  -0.0273   1.0000   0.2053
  -2.000  -0.1734   0.03451   0.02890  -0.0261   1.0000   0.2354
  -1.250  -0.0293   0.02606   0.01776  -0.0330   0.9872   0.1040
  -1.000   0.0134   0.02404   0.01542  -0.0356   0.9807   0.1017
  -0.750   0.0569   0.02298   0.01394  -0.0383   0.9724   0.1050
  -0.500   0.0985   0.02175   0.01255  -0.0408   0.9637   0.1070
  -0.250   0.1466   0.02104   0.01178  -0.0446   0.9560   0.1160
   0.000   0.1891   0.02018   0.01099  -0.0474   0.9444   0.1247
   0.250   0.2337   0.01939   0.01027  -0.0502   0.9323   0.1386
   0.500   0.2807   0.01856   0.00966  -0.0535   0.9207   0.1990
   0.750   0.3693   0.01629   0.00897  -0.0653   0.9179   1.0000
   1.000   0.4162   0.01614   0.00867  -0.0687   0.9057   1.0000
   1.250   0.4649   0.01587   0.00831  -0.0723   0.8941   1.0000
   1.500   0.5096   0.01557   0.00797  -0.0750   0.8820   1.0000
   1.750   0.5499   0.01527   0.00765  -0.0767   0.8683   1.0000
   2.000   0.5852   0.01501   0.00738  -0.0774   0.8527   1.0000
   2.250   0.6183   0.01476   0.00712  -0.0775   0.8359   1.0000
   2.500   0.6506   0.01449   0.00685  -0.0774   0.8184   1.0000
   2.750   0.6787   0.01432   0.00671  -0.0765   0.7981   1.0000
   3.000   0.7067   0.01416   0.00653  -0.0756   0.7764   1.0000
   3.250   0.7325   0.01409   0.00644  -0.0743   0.7520   1.0000
   3.500   0.7583   0.01407   0.00638  -0.0731   0.7257   1.0000
   3.750   0.7832   0.01414   0.00643  -0.0717   0.6968   1.0000
   4.000   0.8072   0.01429   0.00651  -0.0702   0.6658   1.0000
   4.250   0.8307   0.01454   0.00663  -0.0687   0.6332   1.0000
   4.500   0.8522   0.01487   0.00686  -0.0669   0.5970   1.0000
   4.750   0.8739   0.01528   0.00715  -0.0653   0.5624   1.0000
   5.000   0.8950   0.01576   0.00754  -0.0636   0.5289   1.0000
   5.250   0.9167   0.01629   0.00800  -0.0622   0.4998   1.0000
   5.500   0.9387   0.01685   0.00852  -0.0609   0.4740   1.0000
   5.750   0.9606   0.01740   0.00901  -0.0596   0.4498   1.0000
   6.000   0.9811   0.01788   0.00954  -0.0581   0.4241   1.0000
   6.250   0.9995   0.01828   0.00990  -0.0562   0.3952   1.0000
   6.500   1.0169   0.01868   0.01029  -0.0542   0.3645   1.0000
   6.750   1.0325   0.01906   0.01069  -0.0520   0.3294   1.0000
   7.000   1.0477   0.01951   0.01115  -0.0498   0.2920   1.0000
   7.250   1.0594   0.02010   0.01171  -0.0469   0.2190   1.0000
   7.500   1.0562   0.02322   0.01354  -0.0424   0.0768   1.0000
   7.750   1.0654   0.02508   0.01534  -0.0394   0.0621   1.0000
   8.000   1.0720   0.02708   0.01734  -0.0361   0.0562   1.0000
   8.250   1.0849   0.02872   0.01913  -0.0336   0.0526   1.0000
   8.500   1.0998   0.03059   0.02103  -0.0315   0.0490   1.0000
   8.750   1.1203   0.03378   0.02409  -0.0307   0.0447   1.0000
   9.000   1.1426   0.03585   0.02643  -0.0295   0.0430   1.0000
   9.250   1.1656   0.03867   0.02960  -0.0285   0.0422   1.0000
   9.500   1.1844   0.04180   0.03309  -0.0271   0.0421   1.0000
   9.750   1.1974   0.04531   0.03702  -0.0251   0.0423   1.0000
  10.000   1.2053   0.04902   0.04115  -0.0227   0.0428   1.0000
  10.250   1.2076   0.05261   0.04515  -0.0200   0.0430   1.0000
  10.500   1.2057   0.05642   0.04933  -0.0172   0.0434   1.0000
  10.750   1.1982   0.05971   0.05298  -0.0140   0.0432   1.0000
  11.000   1.1887   0.06370   0.05723  -0.0112   0.0438   1.0000
  11.250   1.1717   0.06664   0.06042  -0.0077   0.0437   1.0000
  11.500   1.1556   0.07067   0.06465  -0.0056   0.0441   1.0000
  11.750   1.1358   0.07439   0.06859  -0.0042   0.0441   1.0000
  12.000   1.0396   0.07332   0.06793   0.0011   0.0456   1.0000
  12.250   1.0060   0.07757   0.07248   0.0002   0.0468   1.0000
  12.500   0.9465   0.08678   0.08204  -0.0053   0.0485   1.0000
  12.750   0.9097   0.09551   0.09092  -0.0107   0.0489   1.0000
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