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GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 14K AIRFOIL (goe14k-il)
Reynolds number: 100,000
Max Cl/Cd: 36.02 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe14k-il-100000.txt
Download as CSV file: xf-goe14k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14K 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5559   0.10934   0.10472  -0.0244   1.0000   0.1301
  -8.750  -0.5653   0.10651   0.10194  -0.0236   1.0000   0.1338
  -8.500  -0.6005   0.10305   0.09858  -0.0252   1.0000   0.1374
  -8.250  -0.6399   0.10012   0.09571  -0.0244   1.0000   0.1380
  -8.000  -0.6836   0.09803   0.09364  -0.0205   1.0000   0.1385
  -7.750  -0.7310   0.09550   0.09097  -0.0170   1.0000   0.1391
  -7.500  -0.6675   0.09128   0.08694  -0.0151   1.0000   0.1455
  -7.250  -0.6896   0.08842   0.08405  -0.0123   1.0000   0.1503
  -7.000  -0.7528   0.08606   0.08137  -0.0085   1.0000   0.1541
  -6.750  -0.7232   0.08141   0.07697  -0.0068   1.0000   0.1577
  -6.500  -0.7234   0.07900   0.07453  -0.0038   1.0000   0.1642
  -6.000  -0.7362   0.07310   0.06850   0.0024   1.0000   0.1792
  -5.750  -0.7963   0.05507   0.04842   0.0118   1.0000   0.0955
  -5.500  -0.7841   0.05196   0.04566   0.0129   1.0000   0.1000
  -5.250  -0.7859   0.04680   0.03985   0.0187   1.0000   0.0890
  -5.000  -0.7904   0.04289   0.03469   0.0267   1.0000   0.0820
  -4.750  -0.7814   0.04047   0.03184   0.0305   1.0000   0.0819
  -4.500  -0.7694   0.03768   0.02912   0.0326   1.0000   0.0861
  -4.250  -0.7563   0.03597   0.02710   0.0355   1.0000   0.0881
  -4.000  -0.7414   0.03412   0.02485   0.0385   1.0000   0.0901
  -3.750  -0.7250   0.03272   0.02303   0.0412   1.0000   0.0932
  -3.500  -0.7067   0.03119   0.02117   0.0431   1.0000   0.0980
  -3.250  -0.6857   0.03004   0.01993   0.0443   1.0000   0.1026
  -3.000  -0.6644   0.02921   0.01886   0.0457   1.0000   0.1083
  -2.750  -0.6404   0.02813   0.01777   0.0461   1.0000   0.1145
  -2.500  -0.6182   0.02754   0.01706   0.0471   1.0000   0.1225
  -2.250  -0.5940   0.02680   0.01636   0.0475   1.0000   0.1298
  -2.000  -0.5716   0.02638   0.01587   0.0484   1.0000   0.1395
  -1.750  -0.2133   0.02963   0.02276  -0.0209   1.0000   1.0000
  -1.500  -0.1965   0.02983   0.02274  -0.0194   1.0000   1.0000
  -1.250  -0.1795   0.03006   0.02277  -0.0178   1.0000   1.0000
  -1.000  -0.1625   0.03031   0.02283  -0.0163   1.0000   1.0000
  -0.750  -0.1453   0.03059   0.02296  -0.0148   1.0000   1.0000
  -0.500  -0.1281   0.03090   0.02311  -0.0134   1.0000   1.0000
  -0.250  -0.1109   0.03123   0.02332  -0.0120   1.0000   1.0000
   0.000  -0.0936   0.03159   0.02355  -0.0106   1.0000   1.0000
   0.250  -0.0763   0.03197   0.02384  -0.0093   1.0000   1.0000
   0.500  -0.0591   0.03238   0.02417  -0.0080   1.0000   1.0000
   0.750  -0.0418   0.03281   0.02452  -0.0067   1.0000   1.0000
   1.000  -0.0246   0.03327   0.02490  -0.0055   1.0000   1.0000
   1.250  -0.0074   0.03376   0.02534  -0.0043   1.0000   1.0000
   1.500   0.0097   0.03428   0.02581  -0.0031   1.0000   1.0000
   1.750   0.0268   0.03482   0.02631  -0.0020   1.0000   1.0000
   2.000   0.0438   0.03540   0.02686  -0.0009   1.0000   1.0000
   2.250   0.0607   0.03601   0.02744   0.0002   1.0000   1.0000
   2.500   0.0847   0.03659   0.02803  -0.0004   0.9976   1.0000
   2.750   0.1801   0.03738   0.02889  -0.0156   0.9597   1.0000
   3.000   0.2207   0.03772   0.02927  -0.0189   0.9445   1.0000
   3.250   0.2585   0.03807   0.02967  -0.0216   0.9311   1.0000
   3.500   0.2933   0.03840   0.03006  -0.0236   0.9189   1.0000
   3.750   0.3282   0.03873   0.03046  -0.0256   0.9073   1.0000
   4.000   0.3727   0.03918   0.03100  -0.0292   0.8977   1.0000
   4.250   0.4046   0.03925   0.03117  -0.0303   0.8849   1.0000
   4.500   0.4461   0.03909   0.03114  -0.0328   0.8704   1.0000
   4.750   0.4942   0.03812   0.03031  -0.0356   0.8492   1.0000
   5.000   0.5457   0.03695   0.02933  -0.0387   0.8313   1.0000
   5.250   0.6454   0.03293   0.02562  -0.0476   0.8099   1.0000
   5.500   0.6791   0.03149   0.02437  -0.0470   0.7908   1.0000
   5.750   0.7167   0.02978   0.02288  -0.0468   0.7718   1.0000
   6.000   0.7658   0.02693   0.02032  -0.0474   0.7500   1.0000
   6.500   0.8378   0.02326   0.01426  -0.0422   0.2782   1.0000
   6.750   0.8367   0.02514   0.01532  -0.0373   0.1958   1.0000
   7.000   0.8468   0.02645   0.01633  -0.0342   0.1639   1.0000
   7.250   0.8616   0.02758   0.01729  -0.0320   0.1440   1.0000
   7.500   0.8832   0.02889   0.01836  -0.0312   0.1261   1.0000
   7.750   0.9121   0.03017   0.01955  -0.0315   0.1114   1.0000
   8.000   0.9511   0.03183   0.02116  -0.0337   0.0974   1.0000
   8.250   0.9859   0.03332   0.02282  -0.0349   0.0881   1.0000
   8.500   1.0445   0.03620   0.02589  -0.0410   0.0789   1.0000
   8.750   1.1123   0.04053   0.03033  -0.0498   0.0710   1.0000
   9.000   1.1240   0.04224   0.03249  -0.0464   0.0692   1.0000
   9.250   1.1387   0.04484   0.03556  -0.0438   0.0677   1.0000
   9.500   1.1473   0.04763   0.03878  -0.0402   0.0666   1.0000
   9.750   1.1497   0.05010   0.04161  -0.0357   0.0653   1.0000
  10.000   1.1492   0.05251   0.04434  -0.0310   0.0641   1.0000
  10.250   1.1433   0.05509   0.04724  -0.0254   0.0638   1.0000
  10.500   1.1306   0.05776   0.05022  -0.0188   0.0637   1.0000
  10.750   1.1122   0.06083   0.05363  -0.0116   0.0649   1.0000
  11.000   1.0933   0.06394   0.05703  -0.0050   0.0660   1.0000
  11.250   1.0740   0.06726   0.06060   0.0010   0.0673   1.0000
  11.500   1.0563   0.07075   0.06429   0.0061   0.0685   1.0000
  11.750   1.0490   0.07503   0.06868   0.0092   0.0700   1.0000
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