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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.28 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe426-il-1000000-n5.txt
Download as CSV file: xf-goe426-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5083   0.03878   0.03635  -0.1114   0.8791   0.0202
 -11.000  -0.6143   0.02731   0.02389  -0.1088   0.8348   0.0207
 -10.750  -0.6083   0.02511   0.02134  -0.1076   0.8117   0.0209
 -10.500  -0.5953   0.02355   0.01949  -0.1066   0.7890   0.0211
 -10.250  -0.5785   0.02237   0.01807  -0.1059   0.7696   0.0211
 -10.000  -0.5591   0.02142   0.01691  -0.1052   0.7541   0.0212
  -9.750  -0.5419   0.01990   0.01514  -0.1046   0.7421   0.0214
  -9.500  -0.5218   0.01878   0.01384  -0.1041   0.7314   0.0217
  -9.250  -0.4984   0.01816   0.01312  -0.1037   0.7219   0.0219
  -9.000  -0.4741   0.01769   0.01255  -0.1034   0.7134   0.0220
  -8.750  -0.4494   0.01720   0.01198  -0.1032   0.7048   0.0222
  -8.500  -0.4246   0.01672   0.01139  -0.1029   0.6966   0.0223
  -8.250  -0.3996   0.01620   0.01077  -0.1027   0.6877   0.0225
  -8.000  -0.3744   0.01570   0.01017  -0.1024   0.6793   0.0227
  -7.750  -0.3490   0.01520   0.00957  -0.1022   0.6704   0.0228
  -7.500  -0.3234   0.01471   0.00897  -0.1019   0.6624   0.0230
  -7.250  -0.2975   0.01427   0.00844  -0.1017   0.6533   0.0232
  -7.000  -0.2715   0.01382   0.00790  -0.1015   0.6444   0.0234
  -6.750  -0.2455   0.01341   0.00738  -0.1013   0.6337   0.0236
  -6.500  -0.2192   0.01301   0.00689  -0.1011   0.6224   0.0238
  -6.250  -0.1929   0.01265   0.00643  -0.1009   0.6109   0.0240
  -6.000  -0.1666   0.01232   0.00600  -0.1007   0.5995   0.0242
  -5.750  -0.1399   0.01201   0.00561  -0.1005   0.5888   0.0244
  -5.500  -0.1132   0.01172   0.00524  -0.1003   0.5791   0.0246
  -5.000  -0.0593   0.01124   0.00461  -0.1000   0.5608   0.0251
  -4.750  -0.0323   0.01104   0.00434  -0.0999   0.5531   0.0252
  -4.500  -0.0047   0.01087   0.00412  -0.0998   0.5471   0.0254
  -4.250   0.0221   0.01055   0.00374  -0.0996   0.5407   0.0259
  -4.000   0.0491   0.01031   0.00346  -0.0995   0.5350   0.0263
  -3.750   0.0768   0.01012   0.00324  -0.0995   0.5303   0.0266
  -3.500   0.1044   0.00997   0.00307  -0.0994   0.5255   0.0270
  -3.000   0.1599   0.00972   0.00276  -0.0993   0.5165   0.0277
  -2.750   0.1879   0.00960   0.00261  -0.0993   0.5124   0.0281
  -2.500   0.2157   0.00950   0.00248  -0.0993   0.5079   0.0285
  -2.000   0.2716   0.00932   0.00225  -0.0992   0.5001   0.0294
  -1.750   0.2998   0.00923   0.00215  -0.0992   0.4966   0.0299
  -1.500   0.3278   0.00917   0.00206  -0.0992   0.4929   0.0303
  -1.250   0.3557   0.00909   0.00195  -0.0992   0.4893   0.0312
  -1.000   0.3836   0.00903   0.00189  -0.0992   0.4858   0.0324
  -0.750   0.4119   0.00897   0.00184  -0.0992   0.4831   0.0337
  -0.500   0.4402   0.00893   0.00180  -0.0993   0.4798   0.0348
  -0.250   0.4683   0.00890   0.00176  -0.0993   0.4763   0.0359
   0.000   0.4962   0.00887   0.00173  -0.0992   0.4728   0.0386
   0.250   0.5242   0.00886   0.00172  -0.0992   0.4697   0.0417
   0.500   0.5524   0.00882   0.00170  -0.0993   0.4669   0.0474
   0.750   0.5805   0.00877   0.00169  -0.0993   0.4635   0.0593
   1.250   0.6337   0.00803   0.00172  -0.0994   0.4566   0.3620
   1.500   0.6610   0.00793   0.00177  -0.0993   0.4534   0.4222
   1.750   0.6885   0.00779   0.00182  -0.0993   0.4503   0.4918
   2.000   0.7157   0.00769   0.00190  -0.0993   0.4463   0.5649
   2.250   0.7426   0.00762   0.00197  -0.0991   0.4422   0.6257
   2.500   0.7688   0.00756   0.00207  -0.0988   0.4386   0.6893
   2.750   0.7960   0.00753   0.00215  -0.0987   0.4354   0.7283
   3.000   0.8232   0.00754   0.00222  -0.0985   0.4312   0.7554
   3.250   0.8496   0.00754   0.00231  -0.0982   0.4265   0.7920
   3.500   0.8744   0.00751   0.00240  -0.0976   0.4219   0.8405
   3.750   0.9058   0.00734   0.00249  -0.0982   0.4179   0.9567
   4.000   0.9408   0.00743   0.00257  -0.0998   0.4128   1.0000
   4.250   0.9675   0.00757   0.00267  -0.0996   0.4075   1.0000
   4.500   0.9947   0.00767   0.00276  -0.0996   0.4025   1.0000
   4.750   1.0212   0.00780   0.00287  -0.0994   0.3951   1.0000
   5.000   1.0477   0.00795   0.00298  -0.0992   0.3882   1.0000
   5.250   1.0741   0.00809   0.00311  -0.0990   0.3814   1.0000
   5.500   1.1002   0.00825   0.00325  -0.0987   0.3757   1.0000
   5.750   1.1266   0.00839   0.00338  -0.0985   0.3691   1.0000
   6.000   1.1518   0.00860   0.00355  -0.0982   0.3601   1.0000
   6.250   1.1764   0.00884   0.00374  -0.0977   0.3475   1.0000
   6.500   1.2014   0.00906   0.00392  -0.0973   0.3371   1.0000
   6.750   1.2260   0.00928   0.00412  -0.0969   0.3291   1.0000
   7.000   1.2493   0.00959   0.00436  -0.0962   0.3151   1.0000
   7.500   1.2954   0.01021   0.00487  -0.0948   0.2878   1.0000
   7.750   1.3164   0.01062   0.00519  -0.0938   0.2702   1.0000
   8.000   1.3365   0.01106   0.00554  -0.0927   0.2497   1.0000
   8.250   1.3511   0.01179   0.00607  -0.0907   0.2150   1.0000
   8.500   1.3580   0.01286   0.00685  -0.0875   0.1681   1.0000
   8.750   1.3583   0.01401   0.00774  -0.0832   0.1246   1.0000
   9.000   1.3651   0.01474   0.00838  -0.0798   0.1057   1.0000
   9.250   1.3715   0.01552   0.00907  -0.0765   0.0884   1.0000
   9.500   1.3739   0.01653   0.00995  -0.0729   0.0654   1.0000
   9.750   1.3785   0.01751   0.01085  -0.0698   0.0498   1.0000
  10.000   1.3844   0.01849   0.01179  -0.0671   0.0390   1.0000
  10.250   1.3883   0.01964   0.01289  -0.0644   0.0274   1.0000
  10.500   1.3942   0.02078   0.01402  -0.0621   0.0205   1.0000
  10.750   1.4027   0.02183   0.01509  -0.0603   0.0178   1.0000
  11.000   1.4111   0.02296   0.01624  -0.0586   0.0161   1.0000
  11.250   1.4196   0.02415   0.01747  -0.0571   0.0149   1.0000
  11.500   1.4287   0.02536   0.01872  -0.0558   0.0141   1.0000
  11.750   1.4370   0.02670   0.02011  -0.0545   0.0134   1.0000
  12.000   1.4441   0.02820   0.02165  -0.0534   0.0128   1.0000
  12.250   1.4497   0.02990   0.02340  -0.0523   0.0122   1.0000
  12.500   1.4559   0.03161   0.02516  -0.0513   0.0118   1.0000
  12.750   1.4626   0.03333   0.02694  -0.0505   0.0115   1.0000
  13.000   1.4681   0.03520   0.02887  -0.0498   0.0112   1.0000
  13.250   1.4729   0.03719   0.03092  -0.0491   0.0108   1.0000
  13.500   1.4770   0.03930   0.03309  -0.0485   0.0106   1.0000
  13.750   1.4799   0.04159   0.03544  -0.0480   0.0102   1.0000
  14.000   1.4822   0.04401   0.03792  -0.0475   0.0099   1.0000
  14.250   1.4826   0.04670   0.04066  -0.0472   0.0095   1.0000
  14.500   1.4827   0.04949   0.04353  -0.0470   0.0093   1.0000
  14.750   1.4839   0.05225   0.04635  -0.0469   0.0091   1.0000
  15.000   1.4863   0.05490   0.04907  -0.0469   0.0090   1.0000
  15.250   1.4874   0.05775   0.05199  -0.0469   0.0088   1.0000
  15.500   1.4882   0.06070   0.05502  -0.0471   0.0086   1.0000
  15.750   1.4888   0.06372   0.05810  -0.0473   0.0085   1.0000
  16.000   1.4886   0.06690   0.06135  -0.0476   0.0083   1.0000
  16.250   1.4887   0.07006   0.06458  -0.0480   0.0081   1.0000
  16.500   1.4881   0.07336   0.06795  -0.0485   0.0080   1.0000
  16.750   1.4867   0.07686   0.07153  -0.0491   0.0078   1.0000
  17.000   1.4863   0.08025   0.07498  -0.0497   0.0077   1.0000
  17.250   1.4848   0.08383   0.07863  -0.0505   0.0075   1.0000
  17.500   1.4821   0.08765   0.08252  -0.0514   0.0074   1.0000
  17.750   1.4794   0.09154   0.08648  -0.0524   0.0072   1.0000
  18.000   1.4758   0.09564   0.09065  -0.0535   0.0071   1.0000
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