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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.92 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe426-il-1000000.txt
Download as CSV file: xf-goe426-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1329   0.08347   0.08171  -0.0710   0.9271   0.0250
 -10.250  -0.1270   0.08029   0.07845  -0.0722   0.9067   0.0254
 -10.000  -0.1233   0.07723   0.07531  -0.0729   0.8829   0.0259
  -9.750  -0.1222   0.07392   0.07189  -0.0736   0.8575   0.0265
  -9.500  -0.1437   0.06505   0.06297  -0.0785   0.8406   0.0284
  -9.250  -0.1502   0.05987   0.05771  -0.0805   0.8190   0.0284
  -9.000  -0.1657   0.05255   0.05032  -0.0839   0.8009   0.0285
  -8.750  -0.2612   0.04871   0.04634  -0.1056   0.8368   0.0285
  -8.500  -0.3039   0.04027   0.03755  -0.1067   0.8082   0.0289
  -8.250  -0.2935   0.03860   0.03574  -0.1063   0.7872   0.0291
  -8.000  -0.2809   0.03710   0.03411  -0.1060   0.7697   0.0293
  -7.750  -0.2670   0.03557   0.03244  -0.1058   0.7556   0.0295
  -7.500  -0.2520   0.03392   0.03065  -0.1056   0.7434   0.0298
  -7.250  -0.2350   0.03239   0.02898  -0.1054   0.7324   0.0302
  -7.000  -0.2183   0.03043   0.02684  -0.1053   0.7226   0.0309
  -6.750  -0.2222   0.02070   0.01593  -0.1036   0.7149   0.0281
  -6.500  -0.2005   0.01896   0.01392  -0.1031   0.7060   0.0281
  -6.250  -0.1770   0.01774   0.01245  -0.1027   0.6964   0.0282
  -6.000  -0.1508   0.01747   0.01202  -0.1025   0.6873   0.0285
  -5.750  -0.1292   0.01503   0.00930  -0.1020   0.6784   0.0290
  -5.500  -0.1033   0.01419   0.00836  -0.1018   0.6691   0.0293
  -5.250  -0.0772   0.01359   0.00767  -0.1016   0.6590   0.0295
  -5.000  -0.0508   0.01306   0.00705  -0.1014   0.6478   0.0298
  -4.750  -0.0241   0.01260   0.00651  -0.1012   0.6367   0.0301
  -4.500   0.0025   0.01218   0.00601  -0.1010   0.6255   0.0303
  -4.250   0.0292   0.01181   0.00556  -0.1008   0.6136   0.0307
  -4.000   0.0560   0.01144   0.00513  -0.1006   0.6021   0.0310
  -3.750   0.0828   0.01112   0.00473  -0.1004   0.5918   0.0314
  -3.500   0.1096   0.01084   0.00438  -0.1001   0.5820   0.0319
  -3.250   0.1369   0.01060   0.00409  -0.1000   0.5737   0.0325
  -3.000   0.1641   0.01046   0.00388  -0.0998   0.5656   0.0331
  -2.750   0.1916   0.01026   0.00365  -0.0997   0.5590   0.0334
  -2.500   0.2187   0.01002   0.00335  -0.0995   0.5524   0.0338
  -2.250   0.2451   0.00961   0.00290  -0.0993   0.5467   0.0346
  -2.000   0.2727   0.00941   0.00269  -0.0993   0.5416   0.0354
  -1.750   0.3004   0.00930   0.00254  -0.0992   0.5364   0.0362
  -1.500   0.3278   0.00922   0.00242  -0.0991   0.5314   0.0371
  -1.250   0.3561   0.00910   0.00230  -0.0991   0.5277   0.0383
  -1.000   0.3841   0.00903   0.00221  -0.0991   0.5235   0.0393
  -0.750   0.4117   0.00890   0.00205  -0.0990   0.5194   0.0413
  -0.500   0.4393   0.00886   0.00198  -0.0989   0.5151   0.0436
  -0.250   0.4677   0.00879   0.00191  -0.0990   0.5121   0.0460
   0.000   0.4958   0.00870   0.00183  -0.0990   0.5085   0.0509
   0.250   0.5236   0.00857   0.00177  -0.0990   0.5049   0.0774
   0.500   0.5481   0.00776   0.00177  -0.0989   0.5012   0.3793
   0.750   0.5742   0.00743   0.00183  -0.0988   0.4977   0.5186
   1.000   0.6015   0.00728   0.00189  -0.0987   0.4947   0.5983
   1.250   0.6288   0.00720   0.00194  -0.0985   0.4913   0.6472
   1.500   0.6555   0.00714   0.00201  -0.0983   0.4878   0.7020
   1.750   0.6817   0.00713   0.00210  -0.0979   0.4839   0.7521
   2.000   0.7081   0.00708   0.00216  -0.0975   0.4808   0.7967
   2.250   0.7317   0.00688   0.00222  -0.0964   0.4776   0.8743
   2.500   0.7771   0.00678   0.00227  -0.1001   0.4737   1.0000
   2.750   0.8042   0.00688   0.00232  -0.0999   0.4700   1.0000
   3.000   0.8312   0.00700   0.00240  -0.0998   0.4660   1.0000
   3.250   0.8592   0.00705   0.00245  -0.0998   0.4627   1.0000
   3.500   0.8867   0.00712   0.00251  -0.0998   0.4587   1.0000
   3.750   0.9139   0.00723   0.00259  -0.0996   0.4547   1.0000
   4.000   0.9406   0.00736   0.00269  -0.0995   0.4504   1.0000
   4.250   0.9684   0.00742   0.00276  -0.0995   0.4468   1.0000
   4.500   0.9958   0.00750   0.00284  -0.0994   0.4422   1.0000
   4.750   1.0225   0.00763   0.00294  -0.0992   0.4374   1.0000
   5.000   1.0494   0.00774   0.00304  -0.0991   0.4328   1.0000
   5.250   1.0767   0.00782   0.00314  -0.0991   0.4273   1.0000
   5.500   1.1029   0.00797   0.00325  -0.0988   0.4213   1.0000
   5.750   1.1297   0.00808   0.00337  -0.0987   0.4156   1.0000
   6.000   1.1561   0.00820   0.00349  -0.0985   0.4086   1.0000
   6.250   1.1820   0.00836   0.00362  -0.0982   0.4002   1.0000
   6.500   1.2075   0.00853   0.00376  -0.0979   0.3911   1.0000
   6.750   1.2333   0.00869   0.00392  -0.0976   0.3833   1.0000
   7.250   1.2825   0.00913   0.00429  -0.0967   0.3616   1.0000
   7.500   1.3067   0.00936   0.00449  -0.0962   0.3500   1.0000
   7.750   1.3301   0.00964   0.00473  -0.0956   0.3376   1.0000
   8.000   1.3527   0.00995   0.00499  -0.0948   0.3237   1.0000
   8.250   1.3745   0.01030   0.00528  -0.0939   0.3080   1.0000
   8.500   1.3956   0.01067   0.00559  -0.0930   0.2924   1.0000
   8.750   1.4161   0.01107   0.00592  -0.0919   0.2763   1.0000
   9.000   1.4347   0.01154   0.00630  -0.0905   0.2571   1.0000
   9.250   1.4487   0.01221   0.00682  -0.0884   0.2284   1.0000
   9.500   1.4524   0.01325   0.00760  -0.0846   0.1855   1.0000
   9.750   1.4449   0.01453   0.00861  -0.0790   0.1419   1.0000
  10.000   1.4419   0.01572   0.00963  -0.0744   0.1129   1.0000
  10.250   1.4435   0.01679   0.01059  -0.0708   0.0922   1.0000
  10.500   1.4380   0.01830   0.01193  -0.0666   0.0641   1.0000
  10.750   1.4340   0.01988   0.01341  -0.0630   0.0444   1.0000
  11.000   1.4302   0.02162   0.01506  -0.0598   0.0295   1.0000
  11.250   1.4326   0.02313   0.01657  -0.0575   0.0233   1.0000
  11.500   1.4373   0.02460   0.01806  -0.0557   0.0209   1.0000
  11.750   1.4437   0.02605   0.01956  -0.0542   0.0195   1.0000
  12.000   1.4495   0.02761   0.02117  -0.0529   0.0185   1.0000
  12.250   1.4525   0.02950   0.02311  -0.0516   0.0175   1.0000
  12.500   1.4555   0.03148   0.02515  -0.0505   0.0167   1.0000
  12.750   1.4611   0.03329   0.02703  -0.0496   0.0163   1.0000
  13.000   1.4653   0.03530   0.02910  -0.0488   0.0158   1.0000
  13.250   1.4684   0.03746   0.03133  -0.0481   0.0154   1.0000
  13.500   1.4700   0.03983   0.03376  -0.0474   0.0150   1.0000
  13.750   1.4693   0.04253   0.03653  -0.0469   0.0145   1.0000
  14.000   1.4663   0.04556   0.03963  -0.0464   0.0142   1.0000
  14.250   1.4604   0.04902   0.04319  -0.0462   0.0138   1.0000
  14.500   1.4613   0.05181   0.04606  -0.0460   0.0136   1.0000
  14.750   1.4617   0.05471   0.04904  -0.0460   0.0134   1.0000
  15.000   1.4621   0.05766   0.05206  -0.0461   0.0132   1.0000
  15.250   1.4620   0.06074   0.05521  -0.0463   0.0129   1.0000
  15.500   1.4606   0.06405   0.05860  -0.0465   0.0127   1.0000
  15.750   1.4603   0.06726   0.06187  -0.0469   0.0124   1.0000
  16.000   1.4584   0.07072   0.06541  -0.0473   0.0122   1.0000
  16.250   1.4553   0.07441   0.06917  -0.0479   0.0121   1.0000
  16.500   1.4533   0.07803   0.07286  -0.0486   0.0118   1.0000
  16.750   1.4475   0.08222   0.07712  -0.0494   0.0116   1.0000
  17.000   1.4386   0.08697   0.08196  -0.0505   0.0113   1.0000
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