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GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 439 AIRFOIL (goe439-il)
Reynolds number: 500,000
Max Cl/Cd: 108.36 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe439-il-500000.txt
Download as CSV file: xf-goe439-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 439 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  -0.2963   0.09118   0.08908  -0.0291   1.0000   0.0151
  -7.750  -0.2992   0.08912   0.08707  -0.0280   1.0000   0.0152
  -7.500  -0.3058   0.08753   0.08553  -0.0260   1.0000   0.0155
  -7.250  -0.3017   0.08491   0.08295  -0.0274   0.9982   0.0158
  -7.000  -0.2774   0.08053   0.07857  -0.0345   0.9927   0.0174
  -6.750  -0.2378   0.07456   0.07257  -0.0499   0.9852   0.0191
  -6.500  -0.1409   0.04838   0.04647  -0.0657   0.9634   0.0199
  -6.250  -0.1190   0.04447   0.04253  -0.0693   0.9566   0.0205
  -6.000  -0.0980   0.04045   0.03847  -0.0738   0.9439   0.0210
  -5.750  -0.0776   0.03644   0.03439  -0.0783   0.9292   0.0219
  -5.500  -0.0586   0.03243   0.03029  -0.0825   0.9114   0.0231
  -5.250  -0.0377   0.02809   0.02582  -0.0870   0.8940   0.0247
  -5.000  -0.0073   0.02401   0.02150  -0.0921   0.8794   0.0264
  -4.750   0.0150   0.01952   0.01676  -0.0948   0.8656   0.0265
  -4.500   0.0358   0.02120   0.01746  -0.1062   0.8924   0.0186
  -4.250   0.0601   0.01764   0.01321  -0.1060   0.8770   0.0195
  -4.000   0.0836   0.01446   0.00941  -0.1055   0.8623   0.0198
  -3.750   0.1086   0.01281   0.00743  -0.1049   0.8480   0.0210
  -3.500   0.1348   0.01214   0.00657  -0.1044   0.8343   0.0223
  -3.250   0.1612   0.01153   0.00576  -0.1039   0.8210   0.0242
  -3.000   0.1881   0.01144   0.00552  -0.1034   0.8083   0.0264
  -2.750   0.2134   0.01026   0.00415  -0.1028   0.7965   0.0298
  -2.500   0.2399   0.00997   0.00374  -0.1023   0.7846   0.0333
  -2.250   0.2663   0.00968   0.00333  -0.1018   0.7729   0.0375
  -2.000   0.2923   0.00924   0.00284  -0.1014   0.7613   0.0439
  -1.750   0.3191   0.00912   0.00262  -0.1010   0.7501   0.0484
  -1.500   0.3451   0.00877   0.00221  -0.1005   0.7389   0.0569
  -1.250   0.3716   0.00861   0.00198  -0.1001   0.7277   0.0655
  -1.000   0.3981   0.00848   0.00189  -0.0997   0.7158   0.0853
  -0.750   0.4249   0.00844   0.00186  -0.0993   0.7036   0.1170
  -0.500   0.4515   0.00840   0.00180  -0.0990   0.6912   0.1339
  -0.250   0.4780   0.00838   0.00174  -0.0986   0.6782   0.1457
   0.000   0.5045   0.00835   0.00168  -0.0982   0.6645   0.1578
   0.250   0.5307   0.00830   0.00163  -0.0979   0.6500   0.1761
   0.500   0.5563   0.00811   0.00163  -0.0975   0.6346   0.2543
   0.750   0.5937   0.00651   0.00173  -0.0999   0.6178   1.0000
   1.000   0.6192   0.00664   0.00172  -0.0993   0.6011   1.0000
   1.250   0.6447   0.00678   0.00174  -0.0988   0.5843   1.0000
   1.500   0.6702   0.00692   0.00177  -0.0982   0.5680   1.0000
   1.750   0.6957   0.00707   0.00181  -0.0977   0.5525   1.0000
   2.000   0.7213   0.00724   0.00188  -0.0972   0.5375   1.0000
   2.250   0.7468   0.00741   0.00196  -0.0967   0.5228   1.0000
   2.500   0.7722   0.00758   0.00205  -0.0962   0.5082   1.0000
   2.750   0.7977   0.00776   0.00215  -0.0957   0.4934   1.0000
   3.000   0.8233   0.00793   0.00226  -0.0953   0.4807   1.0000
   3.250   0.8488   0.00811   0.00239  -0.0948   0.4692   1.0000
   3.500   0.8744   0.00830   0.00252  -0.0944   0.4576   1.0000
   3.750   0.9001   0.00846   0.00266  -0.0940   0.4461   1.0000
   4.000   0.9258   0.00863   0.00281  -0.0936   0.4349   1.0000
   4.250   0.9510   0.00883   0.00298  -0.0931   0.4212   1.0000
   4.500   0.9761   0.00904   0.00314  -0.0926   0.4070   1.0000
   4.750   1.0012   0.00924   0.00332  -0.0921   0.3942   1.0000
   5.000   1.0258   0.00948   0.00350  -0.0916   0.3768   1.0000
   5.250   1.0500   0.00975   0.00372  -0.0910   0.3586   1.0000
   5.500   1.0744   0.01001   0.00394  -0.0905   0.3417   1.0000
   5.750   1.0985   0.01030   0.00417  -0.0899   0.3218   1.0000
   6.000   1.1218   0.01065   0.00445  -0.0892   0.3001   1.0000
   6.250   1.1435   0.01115   0.00479  -0.0883   0.2625   1.0000
   6.500   1.1593   0.01221   0.00539  -0.0866   0.1841   1.0000
   6.750   1.1604   0.01477   0.00701  -0.0827   0.0346   1.0000
   7.000   1.1800   0.01548   0.00780  -0.0814   0.0265   1.0000
   7.250   1.1984   0.01630   0.00874  -0.0798   0.0221   1.0000
   7.500   1.2182   0.01692   0.00945  -0.0785   0.0202   1.0000
   7.750   1.2361   0.01767   0.01030  -0.0769   0.0185   1.0000
   8.000   1.2511   0.01859   0.01131  -0.0750   0.0170   1.0000
   8.250   1.2567   0.02014   0.01299  -0.0716   0.0157   1.0000
   8.500   1.2675   0.02117   0.01411  -0.0690   0.0149   1.0000
   8.750   1.2792   0.02194   0.01496  -0.0665   0.0142   1.0000
   9.000   1.2858   0.02298   0.01608  -0.0633   0.0136   1.0000
   9.250   1.2911   0.02415   0.01733  -0.0601   0.0132   1.0000
   9.500   1.2965   0.02539   0.01867  -0.0572   0.0127   1.0000
   9.750   1.3021   0.02671   0.02007  -0.0545   0.0123   1.0000
  10.000   1.3068   0.02820   0.02163  -0.0520   0.0118   1.0000
  10.250   1.3115   0.02984   0.02334  -0.0497   0.0115   1.0000
  10.500   1.3165   0.03165   0.02522  -0.0476   0.0112   1.0000
  10.750   1.3230   0.03417   0.02776  -0.0457   0.0107   1.0000
  11.000   1.3377   0.03682   0.03053  -0.0444   0.0102   1.0000
  11.250   1.3457   0.03834   0.03220  -0.0428   0.0100   1.0000
  11.500   1.3548   0.04021   0.03424  -0.0413   0.0097   1.0000
  11.750   1.3653   0.04250   0.03668  -0.0400   0.0096   1.0000
  12.000   1.3750   0.04527   0.03964  -0.0387   0.0095   1.0000
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