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GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 269 AIRFOIL (goe269-il)
Reynolds number: 500,000
Max Cl/Cd: 107.75 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe269-il-500000.txt
Download as CSV file: xf-goe269-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 269 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3571   0.09878   0.09654  -0.0113   1.0000   0.0240
  -8.000  -0.3510   0.09565   0.09343  -0.0137   1.0000   0.0254
  -7.750  -0.3496   0.09285   0.09066  -0.0186   1.0000   0.0258
  -7.500  -0.3392   0.08905   0.08689  -0.0251   1.0000   0.0259
  -7.250  -0.3313   0.08437   0.08223  -0.0272   1.0000   0.0261
  -7.000  -0.3227   0.08159   0.07946  -0.0250   1.0000   0.0265
  -6.750  -0.3135   0.07932   0.07722  -0.0250   1.0000   0.0269
  -6.500  -0.3077   0.07727   0.07520  -0.0251   1.0000   0.0275
  -6.250  -0.2812   0.07358   0.07150  -0.0310   0.9958   0.0287
  -6.000  -0.2210   0.06678   0.06456  -0.0514   0.9874   0.0315
  -5.750  -0.1919   0.06054   0.05827  -0.0583   0.9793   0.0320
  -5.250  -0.1406   0.05522   0.05290  -0.0628   0.9566   0.0335
  -5.000  -0.1108   0.05216   0.04976  -0.0669   0.9405   0.0349
  -4.750  -0.0559   0.04741   0.04469  -0.0781   0.9237   0.0382
  -4.500  -0.0349   0.04240   0.03955  -0.0807   0.9080   0.0390
  -4.250  -0.0151   0.04066   0.03774  -0.0806   0.8912   0.0396
  -4.000   0.0088   0.03881   0.03579  -0.0813   0.8752   0.0405
  -3.750   0.0361   0.03673   0.03358  -0.0828   0.8598   0.0419
  -3.500   0.0812   0.03428   0.03073  -0.0865   0.8451   0.0462
  -3.250   0.1097   0.02943   0.02563  -0.0892   0.8298   0.0472
  -3.000   0.1346   0.02792   0.02404  -0.0897   0.8123   0.0479
  -2.750   0.1613   0.02657   0.02255  -0.0902   0.7950   0.0489
  -2.500   0.1896   0.02517   0.02098  -0.0908   0.7786   0.0505
  -2.250   0.2253   0.02450   0.01990  -0.0910   0.7637   0.0556
  -2.000   0.2607   0.01749   0.01221  -0.0938   0.7527   0.0477
  -1.750   0.2916   0.01519   0.00952  -0.0943   0.7407   0.0450
  -1.500   0.3220   0.01337   0.00730  -0.0947   0.7290   0.0453
  -1.250   0.3513   0.01243   0.00610  -0.0948   0.7181   0.0461
  -1.000   0.3802   0.01141   0.00487  -0.0950   0.7083   0.0478
  -0.750   0.4085   0.01131   0.00473  -0.0949   0.6980   0.0496
  -0.500   0.4371   0.01103   0.00437  -0.0949   0.6880   0.0514
  -0.250   0.4656   0.01076   0.00400  -0.0948   0.6790   0.0537
   0.000   0.4941   0.01065   0.00381  -0.0947   0.6693   0.0558
   0.250   0.5226   0.01022   0.00338  -0.0948   0.6599   0.0596
   0.500   0.5508   0.01023   0.00334  -0.0947   0.6500   0.0639
   0.750   0.5793   0.01004   0.00313  -0.0947   0.6401   0.0689
   1.000   0.6075   0.00995   0.00304  -0.0947   0.6301   0.0738
   1.250   0.6356   0.00994   0.00299  -0.0946   0.6190   0.0783
   1.500   0.6640   0.00972   0.00278  -0.0946   0.6064   0.0836
   1.750   0.6921   0.00969   0.00274  -0.0945   0.5917   0.0886
   2.000   0.7200   0.00970   0.00271  -0.0944   0.5746   0.0924
   2.250   0.7481   0.00960   0.00257  -0.0944   0.5559   0.0971
   2.500   0.7761   0.00961   0.00256  -0.0944   0.5336   0.1018
   2.750   0.8037   0.00970   0.00255  -0.0943   0.5079   0.1055
   3.000   0.8310   0.00983   0.00257  -0.0941   0.4803   0.1103
   3.250   0.8584   0.00997   0.00267  -0.0940   0.4575   0.1185
   3.500   0.8859   0.01011   0.00279  -0.0940   0.4411   0.1382
   3.750   0.9075   0.00871   0.00301  -0.0930   0.4287   1.0000
   4.000   0.9349   0.00894   0.00314  -0.0928   0.4166   1.0000
   4.500   0.9896   0.00936   0.00347  -0.0926   0.3945   1.0000
   4.750   1.0168   0.00957   0.00364  -0.0924   0.3841   1.0000
   5.000   1.0438   0.00980   0.00384  -0.0923   0.3728   1.0000
   5.250   1.0710   0.01000   0.00403  -0.0922   0.3616   1.0000
   5.500   1.0981   0.01021   0.00422  -0.0920   0.3497   1.0000
   5.750   1.1249   0.01044   0.00442  -0.0919   0.3347   1.0000
   6.000   1.1513   0.01071   0.00465  -0.0917   0.3174   1.0000
   6.250   1.1775   0.01102   0.00489  -0.0914   0.2967   1.0000
   6.500   1.2030   0.01141   0.00516  -0.0911   0.2684   1.0000
   6.750   1.2276   0.01192   0.00552  -0.0908   0.2317   1.0000
   7.000   1.2510   0.01262   0.00599  -0.0903   0.1919   1.0000
   7.250   1.2743   0.01329   0.00650  -0.0898   0.1649   1.0000
   7.500   1.2982   0.01385   0.00699  -0.0893   0.1477   1.0000
   7.750   1.3223   0.01435   0.00747  -0.0888   0.1359   1.0000
   8.000   1.3460   0.01488   0.00795  -0.0883   0.1252   1.0000
   8.250   1.3700   0.01534   0.00840  -0.0879   0.1149   1.0000
   8.500   1.3940   0.01579   0.00886  -0.0874   0.1048   1.0000
   8.750   1.4172   0.01630   0.00935  -0.0868   0.0918   1.0000
   9.000   1.4383   0.01705   0.00996  -0.0860   0.0680   1.0000
   9.250   1.4532   0.01853   0.01113  -0.0844   0.0334   1.0000
   9.500   1.4710   0.01959   0.01215  -0.0831   0.0247   1.0000
   9.750   1.4883   0.02064   0.01323  -0.0816   0.0213   1.0000
  10.000   1.5070   0.02145   0.01414  -0.0804   0.0198   1.0000
  10.250   1.5235   0.02241   0.01518  -0.0789   0.0185   1.0000
  10.500   1.5359   0.02369   0.01653  -0.0769   0.0173   1.0000
  10.750   1.5457   0.02505   0.01801  -0.0745   0.0166   1.0000
  11.000   1.5571   0.02611   0.01918  -0.0724   0.0161   1.0000
  11.250   1.5637   0.02729   0.02046  -0.0695   0.0157   1.0000
  11.500   1.5677   0.02863   0.02192  -0.0665   0.0152   1.0000
  11.750   1.5711   0.03016   0.02356  -0.0640   0.0148   1.0000
  12.000   1.5734   0.03195   0.02543  -0.0617   0.0143   1.0000
  12.250   1.5738   0.03406   0.02764  -0.0598   0.0139   1.0000
  12.500   1.5706   0.03669   0.03037  -0.0581   0.0136   1.0000
  12.750   1.5628   0.04001   0.03382  -0.0566   0.0132   1.0000
  13.000   1.5542   0.04366   0.03759  -0.0555   0.0130   1.0000
  13.250   1.5563   0.04627   0.04033  -0.0550   0.0128   1.0000
  13.500   1.5566   0.04919   0.04338  -0.0547   0.0126   1.0000
  13.750   1.5550   0.05237   0.04671  -0.0545   0.0125   1.0000
  14.000   1.5524   0.05577   0.05023  -0.0544   0.0123   1.0000
  14.250   1.5488   0.05935   0.05394  -0.0545   0.0121   1.0000
  14.500   1.5441   0.06310   0.05781  -0.0547   0.0120   1.0000
  14.750   1.5387   0.06701   0.06186  -0.0551   0.0118   1.0000
  15.000   1.5327   0.07109   0.06606  -0.0556   0.0117   1.0000
  15.250   1.5264   0.07533   0.07042  -0.0563   0.0115   1.0000
  15.500   1.5200   0.07973   0.07495  -0.0572   0.0114   1.0000
  15.750   1.5130   0.08433   0.07967  -0.0583   0.0113   1.0000
  16.000   1.5055   0.08912   0.08458  -0.0596   0.0112   1.0000
  16.250   1.4977   0.09408   0.08968  -0.0611   0.0111   1.0000
  16.500   1.4895   0.09922   0.09494  -0.0629   0.0110   1.0000
  16.750   1.4811   0.10449   0.10033  -0.0648   0.0109   1.0000
  17.000   1.4723   0.10991   0.10587  -0.0669   0.0108   1.0000
  17.250   1.4633   0.11548   0.11158  -0.0693   0.0107   1.0000
  17.500   1.4544   0.12115   0.11737  -0.0719   0.0106   1.0000
  17.750   1.4456   0.12690   0.12323  -0.0746   0.0105   1.0000
  18.000   1.4361   0.13286   0.12931  -0.0776   0.0105   1.0000
  18.250   1.4271   0.13880   0.13536  -0.0807   0.0104   1.0000
  18.500   1.4172   0.14516   0.14184  -0.0843   0.0103   1.0000
  18.750   1.4066   0.15187   0.14867  -0.0882   0.0102   1.0000
  19.000   1.3958   0.15887   0.15580  -0.0926   0.0102   1.0000
  19.250   1.3843   0.16634   0.16341  -0.0974   0.0102   1.0000
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