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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 500,000
Max Cl/Cd: 112.68 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe426-il-500000.txt
Download as CSV file: xf-goe426-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2659   0.10524   0.10293  -0.0455   1.0000   0.0320
 -10.250  -0.2851   0.09933   0.09707  -0.0506   1.0000   0.0335
 -10.000  -0.2862   0.09405   0.09181  -0.0550   0.9978   0.0336
  -9.750  -0.2736   0.09015   0.08792  -0.0560   0.9885   0.0340
  -9.500  -0.2535   0.08721   0.08497  -0.0589   0.9824   0.0344
  -9.250  -0.2329   0.08415   0.08191  -0.0624   0.9748   0.0348
  -9.000  -0.2102   0.08036   0.07809  -0.0678   0.9683   0.0355
  -8.750  -0.1877   0.07575   0.07346  -0.0748   0.9583   0.0365
  -8.000  -0.2350   0.04751   0.04457  -0.1065   0.8663   0.0402
  -7.750  -0.2230   0.04558   0.04257  -0.1061   0.8472   0.0405
  -7.500  -0.2120   0.04366   0.04052  -0.1059   0.8281   0.0408
  -7.250  -0.1994   0.04191   0.03864  -0.1056   0.8099   0.0413
  -7.000  -0.1773   0.02851   0.02528  -0.0974   0.7652   0.0421
  -6.750  -0.1676   0.02566   0.02224  -0.0980   0.7539   0.0433
  -6.500  -0.1599   0.03615   0.03176  -0.1051   0.7646   0.0468
  -6.250  -0.1510   0.03042   0.02583  -0.1055   0.7537   0.0480
  -6.000  -0.1298   0.02889   0.02422  -0.1054   0.7424   0.0486
  -5.750  -0.1081   0.02758   0.02278  -0.1052   0.7311   0.0494
  -5.500  -0.0857   0.02631   0.02137  -0.1049   0.7201   0.0506
  -5.250  -0.0626   0.02511   0.01991  -0.1045   0.7098   0.0531
  -5.000  -0.0416   0.02309   0.01744  -0.1041   0.6995   0.0571
  -4.750  -0.0171   0.02198   0.01631  -0.1040   0.6893   0.0584
  -4.500   0.0070   0.01848   0.01214  -0.1028   0.6798   0.0489
  -4.250   0.0332   0.01589   0.00901  -0.1018   0.6698   0.0406
  -4.000   0.0595   0.01516   0.00813  -0.1014   0.6596   0.0405
  -3.750   0.0860   0.01443   0.00730  -0.1011   0.6491   0.0407
  -3.500   0.1124   0.01382   0.00665  -0.1009   0.6393   0.0413
  -3.250   0.1388   0.01339   0.00613  -0.1006   0.6298   0.0421
  -3.000   0.1656   0.01293   0.00563  -0.1004   0.6206   0.0427
  -2.750   0.1921   0.01254   0.00516  -0.1001   0.6124   0.0431
  -2.500   0.2190   0.01217   0.00476  -0.0998   0.6042   0.0437
  -2.000   0.2728   0.01162   0.00410  -0.0994   0.5899   0.0453
  -1.750   0.2997   0.01143   0.00384  -0.0991   0.5833   0.0462
  -1.500   0.3269   0.01125   0.00361  -0.0990   0.5774   0.0471
  -1.250   0.3535   0.01086   0.00322  -0.0988   0.5714   0.0496
  -1.000   0.3806   0.01073   0.00304  -0.0986   0.5659   0.0517
  -0.750   0.4083   0.01062   0.00289  -0.0986   0.5609   0.0540
  -0.500   0.4359   0.01048   0.00273  -0.0985   0.5558   0.0572
  -0.250   0.4634   0.01039   0.00260  -0.0984   0.5510   0.0638
   0.000   0.4889   0.00973   0.00251  -0.0983   0.5466   0.2532
   0.250   0.5126   0.00892   0.00262  -0.0980   0.5424   0.5463
   0.500   0.5383   0.00876   0.00271  -0.0976   0.5381   0.6411
   0.750   0.5640   0.00871   0.00279  -0.0970   0.5338   0.7028
   1.000   0.5892   0.00865   0.00289  -0.0963   0.5298   0.7643
   1.500   0.6395   0.00834   0.00300  -0.0945   0.5219   0.9174
   1.750   0.6876   0.00843   0.00302  -0.0989   0.5171   1.0000
   2.000   0.7148   0.00855   0.00309  -0.0988   0.5132   1.0000
   2.250   0.7421   0.00864   0.00316  -0.0987   0.5092   1.0000
   2.500   0.7694   0.00874   0.00322  -0.0986   0.5052   1.0000
   2.750   0.7965   0.00889   0.00330  -0.0985   0.5011   1.0000
   3.000   0.8237   0.00903   0.00341  -0.0984   0.4971   1.0000
   3.250   0.8508   0.00911   0.00350  -0.0983   0.4930   1.0000
   3.500   0.8780   0.00922   0.00359  -0.0982   0.4889   1.0000
   3.750   0.9049   0.00938   0.00369  -0.0980   0.4849   1.0000
   4.000   0.9319   0.00953   0.00382  -0.0979   0.4807   1.0000
   4.250   0.9588   0.00961   0.00393  -0.0978   0.4761   1.0000
   4.500   0.9855   0.00973   0.00404  -0.0976   0.4716   1.0000
   4.750   1.0122   0.00992   0.00418  -0.0974   0.4674   1.0000
   5.000   1.0388   0.01003   0.00433  -0.0973   0.4630   1.0000
   5.250   1.0652   0.01013   0.00446  -0.0971   0.4581   1.0000
   5.500   1.0914   0.01028   0.00459  -0.0968   0.4533   1.0000
   5.750   1.1176   0.01045   0.00476  -0.0966   0.4485   1.0000
   6.000   1.1436   0.01055   0.00492  -0.0963   0.4429   1.0000
   6.250   1.1691   0.01071   0.00506  -0.0960   0.4374   1.0000
   6.500   1.1946   0.01086   0.00524  -0.0956   0.4316   1.0000
   6.750   1.2198   0.01099   0.00539  -0.0952   0.4248   1.0000
   7.000   1.2440   0.01115   0.00556  -0.0947   0.4169   1.0000
   7.250   1.2685   0.01129   0.00572  -0.0941   0.4086   1.0000
   7.500   1.2924   0.01149   0.00593  -0.0936   0.4013   1.0000
   7.750   1.3157   0.01168   0.00612  -0.0929   0.3916   1.0000
   8.000   1.3386   0.01188   0.00634  -0.0921   0.3808   1.0000
   8.250   1.3603   0.01215   0.00659  -0.0912   0.3695   1.0000
   8.500   1.3807   0.01246   0.00687  -0.0901   0.3563   1.0000
   9.000   1.4194   0.01318   0.00754  -0.0875   0.3292   1.0000
   9.250   1.4380   0.01356   0.00791  -0.0861   0.3159   1.0000
   9.500   1.4543   0.01400   0.00834  -0.0843   0.3013   1.0000
   9.750   1.4668   0.01450   0.00880  -0.0819   0.2855   1.0000
  10.000   1.4762   0.01512   0.00936  -0.0791   0.2671   1.0000
  10.250   1.4823   0.01593   0.01006  -0.0759   0.2412   1.0000
  10.500   1.4792   0.01722   0.01114  -0.0716   0.2038   1.0000
  10.750   1.4669   0.01911   0.01276  -0.0667   0.1596   1.0000
  11.000   1.4538   0.02127   0.01472  -0.0623   0.1257   1.0000
  11.250   1.4433   0.02354   0.01685  -0.0587   0.0998   1.0000
  11.500   1.4323   0.02610   0.01927  -0.0557   0.0725   1.0000
  11.750   1.4181   0.02919   0.02223  -0.0531   0.0502   1.0000
  12.000   1.4093   0.03213   0.02513  -0.0514   0.0374   1.0000
  12.250   1.4052   0.03485   0.02785  -0.0501   0.0316   1.0000
  12.500   1.4030   0.03749   0.03054  -0.0491   0.0286   1.0000
  12.750   1.4029   0.04003   0.03315  -0.0483   0.0269   1.0000
  13.000   1.4004   0.04290   0.03608  -0.0477   0.0255   1.0000
  13.250   1.3956   0.04613   0.03938  -0.0472   0.0244   1.0000
  13.500   1.3958   0.04892   0.04227  -0.0470   0.0236   1.0000
  13.750   1.3944   0.05197   0.04541  -0.0468   0.0227   1.0000
  14.000   1.3922   0.05520   0.04872  -0.0468   0.0221   1.0000
  14.250   1.3884   0.05868   0.05228  -0.0469   0.0214   1.0000
  14.500   1.3813   0.06270   0.05637  -0.0472   0.0208   1.0000
  14.750   1.3737   0.06686   0.06061  -0.0476   0.0203   1.0000
  15.000   1.3730   0.07019   0.06403  -0.0480   0.0200   1.0000
  15.250   1.3712   0.07373   0.06767  -0.0484   0.0196   1.0000
  15.500   1.3696   0.07733   0.07136  -0.0490   0.0191   1.0000
  15.750   1.3675   0.08101   0.07511  -0.0497   0.0187   1.0000
  16.000   1.3650   0.08480   0.07898  -0.0504   0.0184   1.0000
  16.250   1.3628   0.08862   0.08287  -0.0513   0.0181   1.0000
  16.500   1.3610   0.09240   0.08671  -0.0521   0.0178   1.0000
  16.750   1.3577   0.09641   0.09077  -0.0531   0.0174   1.0000
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