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GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 399 AIRFOIL (goe399-il)
Reynolds number: 100,000
Max Cl/Cd: 59.41 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe399-il-100000.txt
Download as CSV file: xf-goe399-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 399 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3672   0.10817   0.10318  -0.0279   1.0000   0.0598
  -8.500  -0.3743   0.10729   0.10241  -0.0300   1.0000   0.0601
  -8.250  -0.3789   0.10578   0.10099  -0.0321   1.0000   0.0603
  -8.000  -0.3784   0.10373   0.09899  -0.0357   1.0000   0.0604
  -7.750  -0.3507   0.09379   0.08900  -0.0271   1.0000   0.0633
  -7.500  -0.3472   0.09103   0.08630  -0.0262   1.0000   0.0661
  -7.250  -0.3498   0.08887   0.08422  -0.0257   1.0000   0.0687
  -7.000  -0.3512   0.08672   0.08215  -0.0271   1.0000   0.0713
  -6.750  -0.3522   0.08527   0.08077  -0.0318   1.0000   0.0732
  -6.500  -0.3481   0.08424   0.07969  -0.0394   1.0000   0.0740
  -6.250  -0.3475   0.07915   0.07472  -0.0362   1.0000   0.0750
  -6.000  -0.3462   0.07557   0.07123  -0.0312   1.0000   0.0766
  -5.750  -0.3440   0.07300   0.06870  -0.0294   1.0000   0.0787
  -5.500  -0.3414   0.07054   0.06627  -0.0290   1.0000   0.0815
  -5.250  -0.3364   0.06814   0.06386  -0.0302   1.0000   0.0848
  -5.000  -0.3195   0.06562   0.06108  -0.0378   1.0000   0.0887
  -4.750  -0.3213   0.06218   0.05777  -0.0337   1.0000   0.0902
  -4.500  -0.3177   0.05980   0.05543  -0.0316   1.0000   0.0929
  -4.250  -0.2913   0.05780   0.05300  -0.0380   1.0000   0.1029
  -4.000  -0.2919   0.05429   0.04973  -0.0342   1.0000   0.1056
  -3.500  -0.2438   0.04828   0.04350  -0.0390   0.9953   0.1231
  -3.250  -0.1977   0.04463   0.03961  -0.0454   0.9871   0.1404
  -3.000  -0.1553   0.04137   0.03614  -0.0506   0.9791   0.1658
  -2.750  -0.1120   0.03892   0.03340  -0.0556   0.9713   0.2049
  -2.500  -0.0817   0.03622   0.03071  -0.0574   0.9633   0.2356
  -2.000   0.0228   0.02988   0.02274  -0.0663   0.9497   0.1612
  -1.750   0.0705   0.02596   0.01800  -0.0683   0.9442   0.1123
  -1.500   0.1094   0.02447   0.01609  -0.0701   0.9365   0.1135
  -1.250   0.1516   0.02290   0.01417  -0.0723   0.9295   0.1115
  -1.000   0.1894   0.02179   0.01280  -0.0738   0.9209   0.1128
  -0.750   0.2339   0.02068   0.01156  -0.0766   0.9145   0.1205
  -0.500   0.2702   0.01995   0.01078  -0.0779   0.9050   0.1298
  -0.250   0.3173   0.01884   0.00977  -0.0811   0.8994   0.1448
   0.000   0.3505   0.01812   0.00919  -0.0818   0.8888   0.1754
   0.250   0.4253   0.01514   0.00816  -0.0906   0.8865   1.0000
   0.500   0.4591   0.01510   0.00790  -0.0913   0.8747   1.0000
   0.750   0.4929   0.01502   0.00768  -0.0919   0.8631   1.0000
   1.000   0.5262   0.01491   0.00746  -0.0923   0.8512   1.0000
   1.250   0.5580   0.01482   0.00727  -0.0923   0.8389   1.0000
   1.500   0.5874   0.01476   0.00714  -0.0919   0.8251   1.0000
   1.750   0.6147   0.01475   0.00707  -0.0911   0.8100   1.0000
   2.000   0.6409   0.01478   0.00703  -0.0900   0.7938   1.0000
   2.250   0.6668   0.01480   0.00699  -0.0889   0.7765   1.0000
   2.500   0.6928   0.01483   0.00697  -0.0877   0.7590   1.0000
   2.750   0.7188   0.01490   0.00697  -0.0866   0.7420   1.0000
   3.000   0.7430   0.01508   0.00711  -0.0853   0.7235   1.0000
   3.250   0.7673   0.01529   0.00730  -0.0842   0.7055   1.0000
   3.500   0.7922   0.01552   0.00753  -0.0832   0.6885   1.0000
   3.750   0.8172   0.01575   0.00775  -0.0823   0.6722   1.0000
   4.000   0.8422   0.01600   0.00800  -0.0813   0.6564   1.0000
   4.250   0.8672   0.01622   0.00820  -0.0804   0.6401   1.0000
   4.500   0.8901   0.01643   0.00850  -0.0791   0.6204   1.0000
   4.750   0.9140   0.01653   0.00860  -0.0778   0.6007   1.0000
   5.000   0.9381   0.01669   0.00874  -0.0766   0.5822   1.0000
   5.250   0.9616   0.01697   0.00911  -0.0755   0.5645   1.0000
   5.500   0.9847   0.01713   0.00934  -0.0742   0.5439   1.0000
   5.750   1.0063   0.01725   0.00947  -0.0725   0.5187   1.0000
   6.000   1.0284   0.01746   0.00970  -0.0710   0.4958   1.0000
   6.250   1.0499   0.01775   0.01007  -0.0696   0.4725   1.0000
   6.500   1.0693   0.01800   0.01035  -0.0676   0.4420   1.0000
   6.750   1.0834   0.01825   0.01062  -0.0647   0.3898   1.0000
   7.000   1.0875   0.01922   0.01099  -0.0605   0.2525   1.0000
   7.250   1.0844   0.02220   0.01274  -0.0564   0.1247   1.0000
   7.500   1.0893   0.02441   0.01478  -0.0531   0.0984   1.0000
   7.750   1.0955   0.02649   0.01677  -0.0498   0.0835   1.0000
   8.000   1.1068   0.02838   0.01860  -0.0473   0.0723   1.0000
   8.250   1.1256   0.03074   0.02089  -0.0458   0.0649   1.0000
   8.500   1.1506   0.03303   0.02321  -0.0451   0.0595   1.0000
   8.750   1.1774   0.03615   0.02640  -0.0450   0.0544   1.0000
   9.000   1.2007   0.03867   0.02924  -0.0439   0.0518   1.0000
   9.250   1.2216   0.04169   0.03262  -0.0426   0.0506   1.0000
   9.500   1.2378   0.04504   0.03639  -0.0408   0.0502   1.0000
   9.750   1.2489   0.04831   0.04007  -0.0387   0.0495   1.0000
  10.000   1.2567   0.05149   0.04361  -0.0365   0.0484   1.0000
  10.250   1.2633   0.05476   0.04719  -0.0345   0.0472   1.0000
  10.500   1.2577   0.05864   0.05159  -0.0312   0.0482   1.0000
  10.750   1.2464   0.06288   0.05630  -0.0278   0.0500   1.0000
  11.000   1.2332   0.06691   0.06066  -0.0246   0.0516   1.0000
  11.250   1.2175   0.07087   0.06484  -0.0218   0.0528   1.0000
  11.500   1.2019   0.07529   0.06945  -0.0200   0.0540   1.0000
  11.750   1.0789   0.07310   0.06774  -0.0135   0.0526   1.0000
  12.000   1.0528   0.07879   0.07360  -0.0141   0.0532   1.0000
  12.250   1.0267   0.08499   0.07996  -0.0156   0.0539   1.0000
  12.500   1.0020   0.09161   0.08671  -0.0177   0.0547   1.0000
  12.750   0.9858   0.09847   0.09364  -0.0196   0.0558   1.0000
  13.000   0.8769   0.11713   0.11270  -0.0359   0.0642   1.0000
  13.250   0.8560   0.12446   0.12005  -0.0396   0.0670   1.0000
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