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GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 15 AIRFOIL (goe15-il)
Reynolds number: 500,000
Max Cl/Cd: 126.37 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe15-il-500000.txt
Download as CSV file: xf-goe15-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 15 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0666   0.10921   0.10711  -0.0530   0.9740   0.0210
 -10.750  -0.0524   0.10558   0.10347  -0.0560   0.9686   0.0215
 -10.500  -0.1587   0.11591   0.11372  -0.0414   0.9936   0.0206
 -10.250  -0.1418   0.11254   0.11034  -0.0448   0.9887   0.0210
 -10.000  -0.1241   0.10907   0.10687  -0.0485   0.9830   0.0217
  -9.750  -0.1091   0.10575   0.10355  -0.0516   0.9732   0.0225
  -9.500  -0.0914   0.10250   0.10029  -0.0568   0.9629   0.0229
  -9.000  -0.0440   0.09404   0.09178  -0.0678   0.9446   0.0232
  -8.750  -0.0089   0.08967   0.08735  -0.0754   0.9355   0.0235
  -8.250   0.0644   0.08153   0.07901  -0.0924   0.9015   0.0251
  -8.000   0.0840   0.07878   0.07612  -0.0964   0.8736   0.0259
  -7.750   0.0886   0.07720   0.07442  -0.0978   0.8428   0.0262
  -7.500   0.0853   0.07613   0.07324  -0.0978   0.8155   0.0263
  -7.000   0.1002   0.07129   0.06823  -0.0983   0.7835   0.0264
  -6.750   0.1099   0.06896   0.06585  -0.0981   0.7720   0.0266
  -6.500   0.1200   0.06692   0.06375  -0.0986   0.7621   0.0268
  -6.250   0.1313   0.06499   0.06175  -0.0993   0.7529   0.0271
  -6.000   0.1440   0.06304   0.05977  -0.1003   0.7447   0.0276
  -5.750   0.1579   0.06105   0.05772  -0.1015   0.7369   0.0283
  -5.500   0.1735   0.05897   0.05557  -0.1030   0.7302   0.0291
  -5.250   0.1894   0.04328   0.03997  -0.0970   0.7084   0.0297
  -4.750   0.2348   0.05243   0.04881  -0.1101   0.7108   0.0299
  -4.500   0.2489   0.05006   0.04643  -0.1098   0.7042   0.0301
  -4.250   0.2666   0.04814   0.04443  -0.1102   0.6974   0.0304
  -4.000   0.2868   0.04627   0.04254  -0.1111   0.6905   0.0309
  -3.750   0.3083   0.04443   0.04063  -0.1120   0.6831   0.0315
  -3.500   0.3312   0.04259   0.03871  -0.1130   0.6762   0.0323
  -3.250   0.3651   0.04119   0.03715  -0.1153   0.6682   0.0334
  -3.000   0.3968   0.03973   0.03545  -0.1169   0.6606   0.0335
  -2.750   0.4115   0.03710   0.03287  -0.1163   0.6515   0.0337
  -2.500   0.4297   0.03525   0.03096  -0.1160   0.6418   0.0340
  -2.250   0.4511   0.03371   0.02937  -0.1159   0.6294   0.0344
  -2.000   0.4740   0.03230   0.02785  -0.1159   0.6151   0.0349
  -1.750   0.4975   0.03097   0.02639  -0.1157   0.5982   0.0357
  -1.500   0.5264   0.03007   0.02526  -0.1155   0.5776   0.0373
  -0.500   0.5925   0.01130   0.00596  -0.1068   0.4808   0.0388
  -0.250   0.6162   0.01075   0.00526  -0.1065   0.4720   0.0397
   0.000   0.6430   0.01030   0.00465  -0.1061   0.4645   0.0414
   0.250   0.6940   0.02374   0.01752  -0.1100   0.4646   0.0420
   1.000   0.7414   0.00832   0.00213  -0.1044   0.4414   0.0438
   1.250   0.7667   0.00804   0.00174  -0.1039   0.4371   0.0457
   1.500   0.7962   0.00795   0.00139  -0.1029   0.4331   0.0473
   1.750   0.8189   0.00735   0.00077  -0.1026   0.4288   0.0479
   2.000   0.8424   0.00707   0.00040  -0.1022   0.4247   0.0487
   2.250   0.8669   0.00686   0.00010  -0.1016   0.4206   0.0503
   2.500   0.9118   0.01797   0.01075  -0.1036   0.4199   0.0528
   2.750   0.9350   0.01678   0.00958  -0.1032   0.4167   0.0538
   3.000   0.9589   0.01634   0.00912  -0.1026   0.4128   0.0550
   3.250   0.9832   0.01612   0.00880  -0.1019   0.4082   0.0575
   3.500   1.0082   0.01597   0.00847  -0.1009   0.4036   0.0606
   3.750   1.0323   0.01554   0.00810  -0.1004   0.3999   0.0623
   4.000   1.0583   0.01606   0.00848  -0.0995   0.3960   0.0675
   4.250   1.0810   0.01515   0.00760  -0.0989   0.3920   0.0702
   6.000   1.2473   0.01460   0.00688  -0.0931   0.3677   0.0770
   6.250   1.2692   0.01435   0.00673  -0.0920   0.3645   0.0727
   6.500   1.2910   0.01432   0.00673  -0.0908   0.3608   0.0727
   6.750   1.3121   0.01436   0.00677  -0.0896   0.3570   0.0731
   7.000   1.3331   0.01454   0.00690  -0.0884   0.3530   0.0732
   7.250   1.3544   0.01454   0.00700  -0.0872   0.3499   0.0740
   7.500   1.3752   0.01461   0.00712  -0.0860   0.3461   0.0755
   7.750   1.3941   0.01469   0.00723  -0.0844   0.3423   0.0784
   8.000   1.4120   0.01486   0.00739  -0.0827   0.3384   0.0810
   8.250   1.4307   0.01504   0.00761  -0.0811   0.3346   0.0839
   8.500   1.4494   0.01517   0.00780  -0.0795   0.3304   0.0883
   8.750   1.4672   0.01535   0.00801  -0.0778   0.3257   0.0995
   9.000   1.5214   0.01478   0.00862  -0.0844   0.3168   1.0000
   9.250   1.5384   0.01500   0.00886  -0.0827   0.3103   1.0000
   9.500   1.5526   0.01537   0.00918  -0.0805   0.3043   1.0000
   9.750   1.5707   0.01560   0.00947  -0.0790   0.2970   1.0000
  10.000   1.5839   0.01603   0.00987  -0.0768   0.2890   1.0000
  10.250   1.6006   0.01637   0.01025  -0.0753   0.2806   1.0000
  10.500   1.6131   0.01690   0.01075  -0.0732   0.2722   1.0000
  10.750   1.6269   0.01741   0.01126  -0.0713   0.2618   1.0000
  11.000   1.6388   0.01804   0.01189  -0.0693   0.2512   1.0000
  11.250   1.6484   0.01882   0.01264  -0.0671   0.2403   1.0000
  11.500   1.6570   0.01971   0.01348  -0.0650   0.2288   1.0000
  11.750   1.6670   0.02057   0.01434  -0.0630   0.2184   1.0000
  12.000   1.6741   0.02164   0.01539  -0.0609   0.2077   1.0000
  12.500   1.6881   0.02396   0.01771  -0.0572   0.1904   1.0000
  12.750   1.6921   0.02542   0.01915  -0.0552   0.1829   1.0000
  13.000   1.6997   0.02669   0.02045  -0.0537   0.1755   1.0000
  13.250   1.7017   0.02844   0.02219  -0.0520   0.1686   1.0000
  13.500   1.7095   0.02980   0.02362  -0.0508   0.1625   1.0000
  13.750   1.7105   0.03178   0.02561  -0.0494   0.1560   1.0000
  14.000   1.7155   0.03348   0.02736  -0.0483   0.1488   1.0000
  14.250   1.7146   0.03576   0.02964  -0.0471   0.1419   1.0000
  14.500   1.7158   0.03791   0.03182  -0.0460   0.1326   1.0000
  14.750   1.7122   0.04058   0.03450  -0.0450   0.1233   1.0000
  15.000   1.7046   0.04376   0.03765  -0.0440   0.1118   1.0000
  15.250   1.6870   0.04810   0.04193  -0.0431   0.0949   1.0000
  15.500   1.6680   0.05285   0.04664  -0.0425   0.0818   1.0000
  15.750   1.6481   0.05791   0.05170  -0.0422   0.0709   1.0000
  16.000   1.6291   0.06313   0.05695  -0.0423   0.0614   1.0000
  16.250   1.6058   0.06908   0.06292  -0.0427   0.0509   1.0000
  16.500   1.5796   0.07566   0.06950  -0.0435   0.0392   1.0000
  16.750   1.5552   0.08214   0.07600  -0.0445   0.0296   1.0000
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