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GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 428 AIRFOIL (goe428-il)
Reynolds number: 500,000
Max Cl/Cd: 104.16 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe428-il-500000.txt
Download as CSV file: xf-goe428-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 428 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2964   0.09178   0.08970  -0.0287   1.0000   0.0147
  -7.750  -0.2982   0.08983   0.08779  -0.0275   1.0000   0.0150
  -7.500  -0.3044   0.08815   0.08616  -0.0257   1.0000   0.0151
  -7.250  -0.3012   0.08562   0.08366  -0.0268   0.9985   0.0154
  -7.000  -0.2771   0.08140   0.07944  -0.0337   0.9934   0.0170
  -6.750  -0.2395   0.07567   0.07369  -0.0478   0.9860   0.0186
  -6.500  -0.2057   0.07052   0.06851  -0.0579   0.9800   0.0188
  -6.250  -0.1718   0.06521   0.06316  -0.0670   0.9735   0.0189
  -6.000  -0.1361   0.05962   0.05749  -0.0760   0.9672   0.0189
  -5.750  -0.1115   0.05251   0.05033  -0.0835   0.9588   0.0197
  -5.500  -0.0820   0.04922   0.04698  -0.0879   0.9477   0.0204
  -5.250  -0.0477   0.04529   0.04294  -0.0937   0.9334   0.0213
  -5.000  -0.0133   0.04110   0.03859  -0.0991   0.9160   0.0231
  -4.750   0.0276   0.03682   0.03400  -0.1038   0.8967   0.0261
  -4.500   0.0545   0.03250   0.02937  -0.1058   0.8787   0.0262
  -3.750   0.1185   0.01647   0.01171  -0.1071   0.8358   0.0221
  -3.500   0.1438   0.01453   0.00932  -0.1064   0.8239   0.0230
  -3.250   0.1698   0.01337   0.00782  -0.1057   0.8122   0.0243
  -2.750   0.2214   0.01136   0.00531  -0.1046   0.7889   0.0289
  -2.500   0.2476   0.01085   0.00469  -0.1041   0.7776   0.0313
  -2.250   0.2741   0.01052   0.00426  -0.1036   0.7664   0.0345
  -2.000   0.3008   0.01035   0.00398  -0.1032   0.7551   0.0365
  -1.750   0.3259   0.00945   0.00295  -0.1025   0.7435   0.0400
  -1.500   0.3520   0.00919   0.00263  -0.1020   0.7307   0.0441
  -1.250   0.3783   0.00898   0.00234  -0.1015   0.7178   0.0471
  -1.000   0.4046   0.00881   0.00208  -0.1010   0.7049   0.0499
  -0.750   0.4309   0.00861   0.00184  -0.1006   0.6924   0.0577
  -0.500   0.4572   0.00847   0.00168  -0.1001   0.6799   0.0751
  -0.250   0.4834   0.00836   0.00171  -0.0997   0.6675   0.1416
   0.000   0.5097   0.00835   0.00166  -0.0994   0.6550   0.1628
   0.250   0.5358   0.00831   0.00162  -0.0990   0.6425   0.1863
   0.500   0.5608   0.00805   0.00166  -0.0986   0.6296   0.3119
   0.750   0.6015   0.00660   0.00176  -0.1017   0.6153   1.0000
   1.000   0.6270   0.00672   0.00177  -0.1011   0.6010   1.0000
   1.250   0.6525   0.00684   0.00178  -0.1005   0.5849   1.0000
   1.500   0.6778   0.00698   0.00180  -0.0999   0.5655   1.0000
   1.750   0.7027   0.00714   0.00184  -0.0992   0.5441   1.0000
   2.000   0.7277   0.00731   0.00189  -0.0986   0.5211   1.0000
   2.250   0.7523   0.00751   0.00196  -0.0979   0.4967   1.0000
   2.500   0.7767   0.00774   0.00205  -0.0972   0.4734   1.0000
   2.750   0.8014   0.00797   0.00217  -0.0966   0.4531   1.0000
   3.000   0.8261   0.00821   0.00230  -0.0960   0.4351   1.0000
   3.250   0.8508   0.00845   0.00246  -0.0955   0.4196   1.0000
   3.500   0.8758   0.00867   0.00261  -0.0949   0.4065   1.0000
   3.750   0.9010   0.00888   0.00277  -0.0944   0.3962   1.0000
   4.250   0.9516   0.00928   0.00314  -0.0935   0.3798   1.0000
   4.500   0.9765   0.00952   0.00333  -0.0930   0.3726   1.0000
   4.750   1.0022   0.00968   0.00352  -0.0927   0.3654   1.0000
   5.000   1.0270   0.00991   0.00372  -0.0921   0.3560   1.0000
   5.250   1.0515   0.01015   0.00393  -0.0916   0.3436   1.0000
   5.500   1.0762   0.01036   0.00413  -0.0911   0.3313   1.0000
   5.750   1.1010   0.01057   0.00434  -0.0906   0.3192   1.0000
   6.000   1.1250   0.01083   0.00456  -0.0900   0.3031   1.0000
   6.250   1.1490   0.01110   0.00481  -0.0894   0.2817   1.0000
   6.500   1.1702   0.01161   0.00512  -0.0884   0.2356   1.0000
   6.750   1.1729   0.01390   0.00645  -0.0849   0.0868   1.0000
   7.000   1.1841   0.01540   0.00761  -0.0823   0.0258   1.0000
   7.250   1.2045   0.01598   0.00830  -0.0810   0.0218   1.0000
   7.500   1.2237   0.01664   0.00906  -0.0796   0.0194   1.0000
   7.750   1.2397   0.01755   0.01008  -0.0777   0.0175   1.0000
   8.000   1.2508   0.01877   0.01145  -0.0750   0.0160   1.0000
   8.250   1.2679   0.01943   0.01218  -0.0734   0.0152   1.0000
   8.500   1.2811   0.02031   0.01315  -0.0711   0.0143   1.0000
   8.750   1.2908   0.02126   0.01419  -0.0683   0.0136   1.0000
   9.000   1.2974   0.02226   0.01527  -0.0650   0.0131   1.0000
   9.250   1.3024   0.02338   0.01648  -0.0617   0.0126   1.0000
   9.500   1.3056   0.02468   0.01786  -0.0584   0.0122   1.0000
   9.750   1.3068   0.02621   0.01948  -0.0552   0.0119   1.0000
  10.000   1.3064   0.02805   0.02140  -0.0521   0.0116   1.0000
  10.250   1.3060   0.03025   0.02366  -0.0492   0.0113   1.0000
  10.500   1.3092   0.03280   0.02630  -0.0468   0.0107   1.0000
  10.750   1.3188   0.03429   0.02790  -0.0452   0.0105   1.0000
  11.000   1.3280   0.03579   0.02951  -0.0438   0.0102   1.0000
  11.250   1.3380   0.03762   0.03146  -0.0423   0.0100   1.0000
  11.500   1.3483   0.03961   0.03357  -0.0409   0.0098   1.0000
  11.750   1.3591   0.04184   0.03597  -0.0396   0.0097   1.0000
  12.000   1.3686   0.04439   0.03869  -0.0382   0.0097   1.0000
  12.250   1.3740   0.04708   0.04158  -0.0369   0.0095   1.0000
  12.500   1.3790   0.05070   0.04543  -0.0355   0.0098   1.0000
  14.500   1.1503   0.09469   0.09163  -0.0347   0.0166   1.0000
  14.750   1.1270   0.09966   0.09675  -0.0377   0.0167   1.0000
  15.000   1.1054   0.10499   0.10225  -0.0413   0.0169   1.0000
  15.250   1.0810   0.11148   0.10891  -0.0457   0.0170   1.0000
  15.500   1.0568   0.11842   0.11604  -0.0510   0.0173   1.0000
  15.750   1.0305   0.12647   0.12425  -0.0568   0.0174   1.0000
  16.000   0.9691   0.14353   0.14165  -0.0700   0.0187   1.0000
  16.250   0.9196   0.16095   0.15924  -0.0816   0.0199   1.0000
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