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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 200,000
Max Cl/Cd: 72.81 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe92-il-200000-n5.txt
Download as CSV file: xf-goe92-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2496   0.10294   0.09980  -0.0259   1.0000   0.0150
  -8.250  -0.2447   0.10025   0.09716  -0.0267   1.0000   0.0152
  -8.000  -0.2418   0.09780   0.09476  -0.0271   1.0000   0.0155
  -7.750  -0.2263   0.09416   0.09113  -0.0310   0.9839   0.0159
  -7.500  -0.2100   0.09049   0.08746  -0.0352   0.9662   0.0163
  -7.250  -0.1940   0.08689   0.08386  -0.0393   0.9498   0.0168
  -7.000  -0.1779   0.08336   0.08030  -0.0436   0.9353   0.0173
  -6.750  -0.1603   0.07980   0.07671  -0.0482   0.9226   0.0180
  -6.250  -0.1198   0.07316   0.06997  -0.0592   0.8978   0.0194
  -6.000  -0.0970   0.06980   0.06652  -0.0650   0.8855   0.0196
  -5.750  -0.0736   0.06630   0.06292  -0.0699   0.8738   0.0197
  -5.500  -0.0501   0.06272   0.05924  -0.0739   0.8628   0.0198
  -5.250  -0.0252   0.05914   0.05554  -0.0776   0.8528   0.0199
  -5.000   0.0021   0.05567   0.05192  -0.0812   0.8423   0.0200
  -4.750   0.0279   0.05225   0.04835  -0.0837   0.8314   0.0201
  -4.500   0.0524   0.04872   0.04468  -0.0857   0.8200   0.0201
  -4.250   0.0766   0.04517   0.04097  -0.0872   0.8076   0.0200
  -4.000   0.0933   0.04126   0.03701  -0.0881   0.7938   0.0194
  -3.750   0.1150   0.03797   0.03357  -0.0892   0.7781   0.0180
  -3.500   0.1434   0.03476   0.03011  -0.0906   0.7604   0.0173
  -3.250   0.1724   0.03181   0.02684  -0.0915   0.7395   0.0175
  -3.000   0.2046   0.02898   0.02355  -0.0917   0.7144   0.0194
  -2.750   0.2328   0.02627   0.02036  -0.0916   0.6859   0.0195
  -2.250   0.2846   0.02261   0.01588  -0.0912   0.6325   0.0220
  -2.000   0.3111   0.02155   0.01446  -0.0909   0.6107   0.0251
  -1.750   0.3393   0.01993   0.01235  -0.0904   0.5930   0.0261
  -1.500   0.3675   0.01875   0.01066  -0.0899   0.5766   0.0299
  -1.250   0.3938   0.01783   0.00953  -0.0897   0.5605   0.0320
  -1.000   0.4210   0.01699   0.00839  -0.0894   0.5451   0.0334
  -0.750   0.4481   0.01661   0.00774  -0.0890   0.5297   0.0371
  -0.500   0.4752   0.01606   0.00694  -0.0886   0.5141   0.0378
  -0.250   0.5019   0.01567   0.00632  -0.0882   0.4981   0.0384
   0.000   0.5282   0.01505   0.00556  -0.0879   0.4820   0.0400
   0.250   0.5543   0.01463   0.00506  -0.0877   0.4658   0.0423
   0.500   0.5805   0.01439   0.00470  -0.0873   0.4504   0.0420
   0.750   0.6066   0.01421   0.00443  -0.0870   0.4361   0.0418
   1.000   0.6328   0.01409   0.00422  -0.0867   0.4230   0.0418
   1.250   0.6590   0.01402   0.00406  -0.0865   0.4113   0.0421
   1.500   0.6851   0.01402   0.00394  -0.0863   0.4011   0.0428
   1.750   0.7116   0.01405   0.00388  -0.0861   0.3919   0.0440
   2.000   0.7378   0.01413   0.00385  -0.0859   0.3835   0.0459
   2.250   0.7641   0.01425   0.00387  -0.0856   0.3752   0.0484
   2.500   0.7903   0.01439   0.00393  -0.0854   0.3677   0.0519
   2.750   0.8164   0.01449   0.00404  -0.0852   0.3607   0.0720
   3.250   0.8685   0.01319   0.00441  -0.0849   0.3504   1.0000
   3.500   0.8945   0.01344   0.00459  -0.0847   0.3462   1.0000
   3.750   0.9201   0.01373   0.00478  -0.0844   0.3424   1.0000
   4.000   0.9464   0.01394   0.00498  -0.0842   0.3380   1.0000
   4.250   0.9723   0.01419   0.00522  -0.0840   0.3338   1.0000
   4.500   0.9979   0.01447   0.00546  -0.0838   0.3302   1.0000
   4.750   1.0235   0.01476   0.00572  -0.0835   0.3270   1.0000
   5.000   1.0495   0.01499   0.00600  -0.0834   0.3233   1.0000
   5.250   1.0751   0.01525   0.00631  -0.0832   0.3192   1.0000
   5.500   1.1003   0.01554   0.00660  -0.0829   0.3153   1.0000
   5.750   1.1255   0.01585   0.00693  -0.0826   0.3119   1.0000
   6.000   1.1509   0.01607   0.00726  -0.0824   0.3059   1.0000
   6.250   1.1746   0.01629   0.00749  -0.0819   0.2927   1.0000
   6.500   1.1983   0.01651   0.00772  -0.0815   0.2768   1.0000
   6.750   1.2217   0.01678   0.00797  -0.0810   0.2571   1.0000
   7.000   1.2438   0.01719   0.00830  -0.0804   0.2224   1.0000
   7.250   1.2516   0.01916   0.00952  -0.0783   0.1263   1.0000
   7.500   1.2676   0.02032   0.01053  -0.0769   0.0967   1.0000
   7.750   1.2724   0.02245   0.01231  -0.0742   0.0196   1.0000
   8.000   1.2893   0.02332   0.01332  -0.0728   0.0158   1.0000
   8.250   1.3052   0.02423   0.01445  -0.0713   0.0140   1.0000
   8.500   1.3199   0.02516   0.01559  -0.0696   0.0128   1.0000
   8.750   1.3324   0.02615   0.01676  -0.0677   0.0115   1.0000
   9.000   1.3412   0.02730   0.01810  -0.0653   0.0109   1.0000
   9.250   1.3478   0.02864   0.01964  -0.0629   0.0104   1.0000
   9.500   1.3517   0.03024   0.02143  -0.0606   0.0100   1.0000
   9.750   1.3526   0.03217   0.02355  -0.0584   0.0096   1.0000
  10.000   1.3495   0.03456   0.02613  -0.0564   0.0093   1.0000
  10.250   1.3408   0.03766   0.02941  -0.0547   0.0089   1.0000
  10.500   1.3273   0.04157   0.03349  -0.0536   0.0087   1.0000
  10.750   1.3194   0.04525   0.03732  -0.0533   0.0084   1.0000
  11.000   1.3195   0.04829   0.04050  -0.0533   0.0081   1.0000
  11.250   1.3139   0.05223   0.04459  -0.0537   0.0078   1.0000
  11.500   1.3063   0.05656   0.04909  -0.0544   0.0077   1.0000
  11.750   1.2986   0.06096   0.05361  -0.0551   0.0076   1.0000
  12.000   1.2914   0.06523   0.05799  -0.0557   0.0075   1.0000
  12.250   1.2852   0.06934   0.06220  -0.0561   0.0074   1.0000
  12.500   1.2803   0.07324   0.06618  -0.0564   0.0073   1.0000
  12.750   1.2771   0.07684   0.06986  -0.0565   0.0072   1.0000
  13.000   1.2761   0.08006   0.07315  -0.0563   0.0071   1.0000
  13.250   1.2774   0.08287   0.07602  -0.0558   0.0069   1.0000
  13.500   1.2810   0.08523   0.07843  -0.0550   0.0068   1.0000
  13.750   1.2864   0.08733   0.08059  -0.0539   0.0067   1.0000
  14.000   1.2918   0.08952   0.08285  -0.0530   0.0066   1.0000
  14.250   1.2963   0.09197   0.08537  -0.0524   0.0064   1.0000
  14.500   1.3016   0.09420   0.08762  -0.0518   0.0061   1.0000
  14.750   1.3111   0.09547   0.08887  -0.0493   0.0057   1.0000
  15.000   1.3065   0.10000   0.09364  -0.0511   0.0055   1.0000
  15.250   1.3048   0.10401   0.09789  -0.0521   0.0054   1.0000
  15.500   1.3045   0.10775   0.10180  -0.0528   0.0053   1.0000
  15.750   1.3030   0.11171   0.10594  -0.0536   0.0053   1.0000
  16.000   1.3000   0.11605   0.11046  -0.0549   0.0052   1.0000
  16.250   1.2959   0.12065   0.11524  -0.0565   0.0052   1.0000
  16.500   1.2908   0.12559   0.12035  -0.0586   0.0052   1.0000
  16.750   1.2849   0.13076   0.12570  -0.0610   0.0052   1.0000
  17.000   1.2783   0.13626   0.13137  -0.0638   0.0052   1.0000
  17.250   1.2710   0.14197   0.13725  -0.0669   0.0052   1.0000
  17.500   1.2635   0.14789   0.14334  -0.0703   0.0053   1.0000
  17.750   1.2556   0.15409   0.14971  -0.0741   0.0053   1.0000
  18.000   1.2480   0.16041   0.15617  -0.0780   0.0053   1.0000
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