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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 200,000
Max Cl/Cd: 74.11 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe401-il-200000.txt
Download as CSV file: xf-goe401-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3143   0.09035   0.08691  -0.0216   1.0000   0.0395
  -7.250  -0.3208   0.08919   0.08583  -0.0235   1.0000   0.0405
  -7.000  -0.3195   0.08772   0.08441  -0.0295   1.0000   0.0409
  -6.750  -0.3131   0.08542   0.08211  -0.0331   1.0000   0.0411
  -6.500  -0.3148   0.08079   0.07757  -0.0295   1.0000   0.0415
  -6.250  -0.3147   0.07800   0.07484  -0.0258   1.0000   0.0420
  -6.000  -0.3186   0.07609   0.07299  -0.0229   1.0000   0.0425
  -5.750  -0.3140   0.07383   0.07076  -0.0225   0.9986   0.0432
  -5.500  -0.2781   0.06962   0.06650  -0.0294   0.9929   0.0452
  -5.250  -0.2024   0.06586   0.06233  -0.0503   0.9839   0.0505
  -5.000  -0.1859   0.05986   0.05641  -0.0516   0.9766   0.0514
  -4.750  -0.1579   0.05618   0.05275  -0.0541   0.9717   0.0527
  -4.500  -0.1275   0.05305   0.04957  -0.0575   0.9624   0.0550
  -4.250  -0.0633   0.05136   0.04736  -0.0683   0.9533   0.0615
  -4.000  -0.0401   0.04549   0.04158  -0.0709   0.9469   0.0629
  -3.750  -0.0116   0.04266   0.03876  -0.0729   0.9389   0.0651
  -3.500   0.0281   0.03993   0.03591  -0.0770   0.9320   0.0693
  -3.250   0.0750   0.03714   0.03268  -0.0820   0.9219   0.0755
  -3.000   0.1080   0.03413   0.02969  -0.0847   0.9136   0.0777
  -2.750   0.1429   0.03203   0.02748  -0.0870   0.9016   0.0820
  -2.500   0.1815   0.03024   0.02525  -0.0891   0.8877   0.0901
  -2.250   0.2075   0.02815   0.02316  -0.0897   0.8727   0.0932
  -1.750   0.2633   0.02535   0.01989  -0.0896   0.8407   0.1065
  -1.500   0.2876   0.02401   0.01844  -0.0891   0.8241   0.1105
  -1.250   0.3149   0.02317   0.01725  -0.0883   0.8074   0.1208
  -1.000   0.3382   0.02173   0.01574  -0.0875   0.7900   0.1243
  -0.750   0.3711   0.01806   0.01116  -0.0855   0.7751   0.0720
  -0.500   0.3960   0.01663   0.00947  -0.0844   0.7561   0.0689
  -0.250   0.4214   0.01561   0.00816  -0.0832   0.7357   0.0683
   0.000   0.4471   0.01452   0.00671  -0.0820   0.7147   0.0657
   0.250   0.4720   0.01385   0.00584  -0.0808   0.6909   0.0650
   0.500   0.4965   0.01339   0.00521  -0.0796   0.6662   0.0656
   0.750   0.5204   0.01305   0.00475  -0.0784   0.6393   0.0672
   1.000   0.5442   0.01282   0.00439  -0.0772   0.6140   0.0696
   1.250   0.5681   0.01272   0.00413  -0.0761   0.5906   0.0735
   1.500   0.5918   0.01258   0.00395  -0.0750   0.5701   0.0818
   1.750   0.6157   0.01248   0.00380  -0.0740   0.5519   0.0949
   2.000   0.6395   0.01235   0.00379  -0.0730   0.5363   0.1725
   2.250   0.6632   0.01228   0.00380  -0.0721   0.5228   0.2448
   2.500   0.7281   0.01107   0.00390  -0.0804   0.5057   1.0000
   2.750   0.7527   0.01136   0.00400  -0.0796   0.4949   1.0000
   3.000   0.7774   0.01160   0.00414  -0.0788   0.4841   1.0000
   3.250   0.8022   0.01187   0.00433  -0.0781   0.4742   1.0000
   3.750   0.8517   0.01244   0.00473  -0.0767   0.4559   1.0000
   4.000   0.8767   0.01277   0.00497  -0.0760   0.4476   1.0000
   4.250   0.9012   0.01303   0.00522  -0.0753   0.4385   1.0000
   4.500   0.9260   0.01336   0.00551  -0.0747   0.4304   1.0000
   4.750   0.9506   0.01366   0.00578  -0.0740   0.4222   1.0000
   5.000   0.9750   0.01397   0.00610  -0.0733   0.4134   1.0000
   5.250   0.9992   0.01428   0.00635  -0.0725   0.4043   1.0000
   5.500   1.0227   0.01452   0.00665  -0.0717   0.3944   1.0000
   5.750   1.0467   0.01484   0.00693  -0.0709   0.3856   1.0000
   6.000   1.0702   0.01507   0.00723  -0.0700   0.3761   1.0000
   6.250   1.0938   0.01536   0.00755  -0.0692   0.3675   1.0000
   6.500   1.1171   0.01561   0.00781  -0.0683   0.3585   1.0000
   6.750   1.1400   0.01585   0.00816  -0.0673   0.3489   1.0000
   7.000   1.1636   0.01618   0.00845  -0.0666   0.3413   1.0000
   7.250   1.1860   0.01639   0.00882  -0.0655   0.3317   1.0000
   7.500   1.2080   0.01660   0.00908  -0.0644   0.3212   1.0000
   7.750   1.2290   0.01677   0.00930  -0.0632   0.3089   1.0000
   8.000   1.2494   0.01693   0.00951  -0.0618   0.2944   1.0000
   8.250   1.2695   0.01713   0.00978  -0.0605   0.2785   1.0000
   8.500   1.2895   0.01740   0.01011  -0.0592   0.2616   1.0000
   8.750   1.3081   0.01777   0.01049  -0.0577   0.2406   1.0000
   9.000   1.3251   0.01829   0.01101  -0.0560   0.2126   1.0000
   9.250   1.3348   0.01942   0.01182  -0.0534   0.1523   1.0000
   9.500   1.3302   0.02184   0.01360  -0.0492   0.0793   1.0000
   9.750   1.3301   0.02373   0.01543  -0.0453   0.0626   1.0000
  10.000   1.3235   0.02563   0.01736  -0.0405   0.0545   1.0000
  10.250   1.3247   0.02700   0.01886  -0.0368   0.0491   1.0000
  10.500   1.3222   0.02866   0.02056  -0.0332   0.0457   1.0000
  10.750   1.3145   0.03086   0.02280  -0.0296   0.0432   1.0000
  11.000   1.3194   0.03233   0.02443  -0.0276   0.0403   1.0000
  11.250   1.3208   0.03419   0.02637  -0.0256   0.0385   1.0000
  11.500   1.3206   0.03632   0.02854  -0.0239   0.0367   1.0000
  11.750   1.3184   0.03887   0.03109  -0.0222   0.0354   1.0000
  12.000   1.3214   0.04115   0.03345  -0.0207   0.0343   1.0000
  12.250   1.3271   0.04313   0.03557  -0.0196   0.0331   1.0000
  12.500   1.3326   0.04521   0.03775  -0.0185   0.0319   1.0000
  12.750   1.3368   0.04738   0.04003  -0.0178   0.0306   1.0000
  13.000   1.3408   0.04963   0.04234  -0.0171   0.0296   1.0000
  13.250   1.3467   0.05188   0.04462  -0.0163   0.0287   1.0000
  13.500   1.3618   0.05427   0.04703  -0.0144   0.0277   1.0000
  13.750   1.3644   0.05694   0.04991  -0.0138   0.0274   1.0000
  14.000   1.3669   0.05980   0.05297  -0.0132   0.0271   1.0000
  14.250   1.3669   0.06304   0.05643  -0.0129   0.0268   1.0000
  14.500   1.3633   0.06668   0.06031  -0.0128   0.0265   1.0000
  14.750   1.3580   0.07062   0.06448  -0.0131   0.0263   1.0000
  15.000   1.3498   0.07487   0.06895  -0.0139   0.0261   1.0000
  15.250   1.3389   0.07957   0.07387  -0.0151   0.0258   1.0000
  15.500   1.3267   0.08462   0.07914  -0.0169   0.0256   1.0000
  15.750   1.3133   0.09000   0.08473  -0.0191   0.0254   1.0000
  16.000   1.2962   0.09643   0.09139  -0.0219   0.0255   1.0000
  16.250   1.2792   0.10305   0.09822  -0.0252   0.0256   1.0000
  16.500   1.2608   0.11020   0.10557  -0.0291   0.0256   1.0000
  16.750   1.2403   0.11814   0.11371  -0.0338   0.0257   1.0000
  17.000   1.2190   0.12666   0.12242  -0.0390   0.0260   1.0000
  17.250   1.1962   0.13597   0.13190  -0.0448   0.0263   1.0000
  17.500   1.1739   0.14573   0.14180  -0.0511   0.0267   1.0000
  17.750   1.1538   0.15543   0.15160  -0.0570   0.0273   1.0000
  18.000   1.1333   0.16586   0.16212  -0.0635   0.0276   1.0000
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