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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 500,000
Max Cl/Cd: 40.19 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe388-il-500000.txt
Download as CSV file: xf-goe388-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3342   0.10732   0.10392  -0.0436   0.7014   0.0275
  -9.750  -0.3291   0.10374   0.10030  -0.0460   0.6891   0.0276
  -9.500  -0.3302   0.09810   0.09465  -0.0482   0.6826   0.0279
  -9.250  -0.3206   0.09519   0.09168  -0.0474   0.6680   0.0283
  -9.000  -0.3098   0.09270   0.08920  -0.0475   0.6709   0.0288
  -8.750  -0.3002   0.09008   0.08665  -0.0485   0.6850   0.0293
  -8.500  -0.2915   0.08733   0.08395  -0.0499   0.6956   0.0301
  -8.250  -0.2831   0.08449   0.08115  -0.0518   0.6990   0.0312
  -8.000  -0.2756   0.08126   0.07793  -0.0548   0.6986   0.0332
  -7.750  -0.2619   0.07670   0.07334  -0.0663   0.6903   0.0349
  -7.500  -0.2447   0.07217   0.06878  -0.0730   0.6905   0.0350
  -7.250  -0.2257   0.06717   0.06375  -0.0798   0.6911   0.0351
  -7.000  -0.2203   0.05996   0.05652  -0.0844   0.6888   0.0361
  -6.750  -0.2030   0.05781   0.05441  -0.0855   0.7009   0.0367
  -6.500  -0.1836   0.05546   0.05204  -0.0875   0.7021   0.0375
  -6.250  -0.1643   0.05285   0.04913  -0.0902   0.6386   0.0384
  -6.000  -0.1539   0.05240   0.04692  -0.0917   0.1433   0.0394
  -5.750  -0.1277   0.04855   0.04288  -0.0966   0.0968   0.0416
  -5.500  -0.0861   0.04344   0.03735  -0.1042   0.0899   0.0447
  -5.250  -0.0679   0.03465   0.02818  -0.1093   0.0870   0.0464
  -4.500   0.0053   0.01699   0.01076  -0.1063   0.0486   0.0498
  -4.250   0.0303   0.01535   0.00894  -0.1073   0.0440   0.0522
  -4.000   0.0597   0.02862   0.02162  -0.1119   0.0407   0.0565
  -3.750   0.0881   0.02798   0.02068  -0.1123   0.0387   0.0572
  -3.500   0.1118   0.02273   0.01510  -0.1141   0.0375   0.0603
  -3.250   0.1411   0.01917   0.01081  -0.1139   0.0366   0.0461
  -3.000   0.1682   0.01871   0.01019  -0.1138   0.0360   0.0455
  -2.750   0.1956   0.01797   0.00930  -0.1139   0.0347   0.0453
  -2.500   0.2221   0.01734   0.00854  -0.1139   0.0337   0.0453
  -2.250   0.2480   0.01682   0.00789  -0.1137   0.0329   0.0453
  -2.000   0.2720   0.01662   0.00758  -0.1133   0.0323   0.0454
  -1.750   0.2953   0.01641   0.00728  -0.1127   0.0320   0.0461
  -1.500   0.3241   0.01555   0.00640  -0.1131   0.0317   0.0476
  -1.250   0.3520   0.01507   0.00589  -0.1133   0.0301   0.0486
  -1.000   0.3773   0.01507   0.00586  -0.1130   0.0293   0.0498
  -0.750   0.4013   0.01529   0.00605  -0.1126   0.0286   0.0512
  -0.500   0.4217   0.01607   0.00675  -0.1115   0.0281   0.0526
  -0.250   0.4430   0.01691   0.00747  -0.1106   0.0279   0.0540
   0.000   0.4702   0.01667   0.00724  -0.1107   0.0278   0.0558
   0.250   0.4990   0.01622   0.00683  -0.1110   0.0274   0.0574
   0.500   0.5258   0.01606   0.00667  -0.1110   0.0268   0.0649
   0.750   0.5507   0.01628   0.00686  -0.1107   0.0263   0.0751
   1.000   0.5754   0.01610   0.00726  -0.1108   0.0259   0.2808
   1.250   0.5913   0.01499   0.00777  -0.1089   0.0256   0.8712
   1.500   0.6181   0.01541   0.00818  -0.1089   0.0254   1.0000
   1.750   0.6426   0.01599   0.00866  -0.1085   0.0251   1.0000
   2.000   0.6673   0.01662   0.00919  -0.1082   0.0250   1.0000
   2.250   0.6924   0.01731   0.00977  -0.1080   0.0248   1.0000
   2.500   0.7180   0.01806   0.01043  -0.1080   0.0247   1.0000
   2.750   0.7442   0.01889   0.01116  -0.1080   0.0246   1.0000
   3.000   0.7711   0.01981   0.01197  -0.1082   0.0245   1.0000
   3.250   0.7984   0.02083   0.01288  -0.1084   0.0244   1.0000
   3.500   0.8260   0.02193   0.01388  -0.1088   0.0243   1.0000
   3.750   0.8537   0.02312   0.01498  -0.1092   0.0243   1.0000
   4.000   0.8811   0.02437   0.01615  -0.1095   0.0242   1.0000
   4.250   0.9083   0.02567   0.01738  -0.1099   0.0242   1.0000
   4.500   0.9352   0.02702   0.01868  -0.1101   0.0242   1.0000
   4.750   0.9617   0.02833   0.01995  -0.1104   0.0242   1.0000
   5.000   0.9878   0.02961   0.02120  -0.1105   0.0242   1.0000
   5.250   1.0135   0.03082   0.02241  -0.1106   0.0241   1.0000
   5.500   1.0388   0.03195   0.02355  -0.1106   0.0241   1.0000
   5.750   1.0638   0.03297   0.02459  -0.1106   0.0242   1.0000
   6.000   1.0886   0.03395   0.02560  -0.1105   0.0242   1.0000
   6.250   1.1132   0.03495   0.02664  -0.1104   0.0242   1.0000
   6.500   1.1386   0.03724   0.02892  -0.1106   0.0241   1.0000
   7.500   1.2337   0.04314   0.03509  -0.1100   0.0240   1.0000
   7.750   1.2558   0.04339   0.03551  -0.1094   0.0240   1.0000
   8.000   1.2761   0.04274   0.03513  -0.1082   0.0239   1.0000
   8.250   1.2895   0.03922   0.03207  -0.1050   0.0225   1.0000
   8.750   1.3256   0.04353   0.03679  -0.1024   0.0177   1.0000
   9.000   1.3437   0.04392   0.03730  -0.1012   0.0149   1.0000
   9.250   1.3644   0.04489   0.03826  -0.1012   0.0142   1.0000
   9.500   1.3775   0.04703   0.04073  -0.0986   0.0126   1.0000
   9.750   1.3947   0.04833   0.04212  -0.0977   0.0119   1.0000
  10.000   1.4140   0.04898   0.04280  -0.0974   0.0116   1.0000
  10.250   1.4204   0.05243   0.04660  -0.0943   0.0111   1.0000
  10.500   1.4252   0.05584   0.05032  -0.0912   0.0107   1.0000
  10.750   1.4285   0.05901   0.05376  -0.0881   0.0105   1.0000
  11.000   1.4313   0.06182   0.05680  -0.0853   0.0103   1.0000
  11.250   1.4359   0.06400   0.05914  -0.0831   0.0100   1.0000
  11.500   1.4468   0.06511   0.06030  -0.0820   0.0097   1.0000
  11.750   1.4566   0.06616   0.06140  -0.0808   0.0094   1.0000
  12.000   1.4511   0.06897   0.06441  -0.0777   0.0093   1.0000
  12.250   1.4375   0.07238   0.06806  -0.0735   0.0093   1.0000
  12.500   1.4196   0.07530   0.07117  -0.0690   0.0093   1.0000
  12.750   1.3994   0.07815   0.07418  -0.0647   0.0093   1.0000
  13.000   1.3543   0.08342   0.07976  -0.0592   0.0096   1.0000
  13.250   1.3432   0.08598   0.08244  -0.0576   0.0095   1.0000
  13.500   1.2634   0.09636   0.09326  -0.0548   0.0104   1.0000
  13.750   1.2378   0.10159   0.09864  -0.0553   0.0105   1.0000
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