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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 500,000
Max Cl/Cd: 102.63 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe623-il-500000.txt
Download as CSV file: xf-goe623-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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  -0.3951   0.09445   0.09217  -0.0376   1.0000   0.0312
  -9.750  -0.5584   0.05335   0.05112  -0.0643   1.0000   0.0240
  -9.500  -0.5953   0.04006   0.03719  -0.0744   0.9916   0.0236
  -9.250  -0.5870   0.03245   0.02874  -0.0794   0.9846   0.0241
  -9.000  -0.5692   0.02800   0.02366  -0.0814   0.9786   0.0249
  -8.750  -0.5415   0.02612   0.02173  -0.0830   0.9743   0.0258
  -8.500  -0.5090   0.02542   0.02105  -0.0847   0.9711   0.0267
  -8.250  -0.4839   0.02396   0.01937  -0.0851   0.9634   0.0277
  -8.000  -0.4568   0.02225   0.01735  -0.0857   0.9578   0.0286
  -7.750  -0.4319   0.02114   0.01596  -0.0855   0.9495   0.0293
  -7.500  -0.4071   0.01946   0.01396  -0.0854   0.9426   0.0302
  -7.250  -0.3841   0.01803   0.01247  -0.0849   0.9338   0.0313
  -7.000  -0.3582   0.01728   0.01163  -0.0847   0.9270   0.0323
  -6.750  -0.3333   0.01653   0.01077  -0.0841   0.9186   0.0332
  -6.500  -0.3077   0.01580   0.00991  -0.0836   0.9114   0.0340
  -6.250  -0.2820   0.01525   0.00925  -0.0832   0.9030   0.0350
  -6.000  -0.2556   0.01486   0.00872  -0.0827   0.8957   0.0358
  -5.750  -0.2307   0.01383   0.00759  -0.0821   0.8875   0.0366
  -5.500  -0.2056   0.01301   0.00670  -0.0816   0.8803   0.0377
  -5.250  -0.1795   0.01252   0.00617  -0.0812   0.8723   0.0389
  -5.000  -0.1531   0.01213   0.00573  -0.0808   0.8647   0.0402
  -4.750  -0.1264   0.01175   0.00529  -0.0805   0.8562   0.0414
  -4.500  -0.0997   0.01140   0.00486  -0.0801   0.8482   0.0424
  -4.250  -0.0726   0.01110   0.00450  -0.0798   0.8395   0.0433
  -4.000  -0.0461   0.01065   0.00398  -0.0794   0.8315   0.0453
  -3.750  -0.0189   0.01035   0.00368  -0.0792   0.8219   0.0480
  -3.500   0.0085   0.01014   0.00340  -0.0789   0.8129   0.0506
  -3.250   0.0359   0.00988   0.00312  -0.0787   0.8024   0.0553
  -3.000   0.0632   0.00960   0.00288  -0.0785   0.7918   0.0696
  -2.750   0.0899   0.00923   0.00273  -0.0783   0.7813   0.1293
  -2.500   0.1176   0.00913   0.00264  -0.0781   0.7692   0.1527
  -2.250   0.1453   0.00903   0.00252  -0.0780   0.7561   0.1664
  -2.000   0.1730   0.00894   0.00241  -0.0779   0.7427   0.1791
  -1.750   0.2007   0.00886   0.00230  -0.0778   0.7291   0.1922
  -1.500   0.2282   0.00877   0.00221  -0.0776   0.7151   0.2088
  -1.250   0.2554   0.00863   0.00213  -0.0775   0.7014   0.2432
  -1.000   0.2821   0.00841   0.00208  -0.0774   0.6876   0.3169
  -0.750   0.3080   0.00808   0.00204  -0.0771   0.6731   0.4275
  -0.500   0.3323   0.00759   0.00205  -0.0766   0.6596   0.5980
  -0.250   0.3528   0.00703   0.00214  -0.0748   0.6481   0.7987
   0.000   0.3750   0.00689   0.00223  -0.0728   0.6371   0.9189
   0.250   0.4125   0.00698   0.00225  -0.0745   0.6245   0.9674
   0.500   0.4581   0.00710   0.00226  -0.0783   0.6123   0.9908
   0.750   0.5028   0.00718   0.00227  -0.0819   0.6023   1.0000
   1.000   0.5279   0.00729   0.00228  -0.0814   0.5944   1.0000
   1.250   0.5535   0.00735   0.00230  -0.0809   0.5861   1.0000
   1.500   0.5789   0.00747   0.00233  -0.0804   0.5790   1.0000
   1.750   0.6047   0.00753   0.00238  -0.0799   0.5715   1.0000
   2.250   0.6562   0.00773   0.00248  -0.0790   0.5560   1.0000
   2.500   0.6819   0.00786   0.00254  -0.0786   0.5481   1.0000
   2.750   0.7083   0.00793   0.00261  -0.0783   0.5397   1.0000
   3.000   0.7343   0.00806   0.00268  -0.0779   0.5319   1.0000
   3.250   0.7609   0.00815   0.00277  -0.0776   0.5230   1.0000
   3.500   0.7872   0.00828   0.00285  -0.0773   0.5143   1.0000
   3.750   0.8136   0.00839   0.00294  -0.0770   0.5040   1.0000
   4.000   0.8400   0.00851   0.00305  -0.0768   0.4926   1.0000
   4.250   0.8661   0.00865   0.00316  -0.0764   0.4800   1.0000
   4.500   0.8921   0.00880   0.00327  -0.0761   0.4658   1.0000
   4.750   0.9179   0.00897   0.00341  -0.0758   0.4491   1.0000
   5.000   0.9432   0.00919   0.00355  -0.0753   0.4284   1.0000
   5.250   0.9676   0.00946   0.00373  -0.0748   0.4027   1.0000
   5.500   0.9910   0.00983   0.00397  -0.0741   0.3730   1.0000
   5.750   1.0138   0.01026   0.00425  -0.0733   0.3443   1.0000
   6.000   1.0364   0.01072   0.00457  -0.0726   0.3190   1.0000
   6.250   1.0595   0.01114   0.00490  -0.0719   0.2977   1.0000
   6.500   1.0825   0.01156   0.00525  -0.0712   0.2796   1.0000
   6.750   1.1057   0.01196   0.00559  -0.0705   0.2647   1.0000
   7.000   1.1287   0.01236   0.00594  -0.0699   0.2518   1.0000
   7.250   1.1513   0.01277   0.00630  -0.0691   0.2399   1.0000
   7.500   1.1738   0.01319   0.00666  -0.0684   0.2284   1.0000
   7.750   1.1972   0.01352   0.00699  -0.0678   0.2187   1.0000
   8.000   1.2194   0.01392   0.00737  -0.0671   0.2104   1.0000
   8.250   1.2423   0.01427   0.00773  -0.0664   0.2024   1.0000
   8.500   1.2642   0.01466   0.00813  -0.0656   0.1957   1.0000
   8.750   1.2868   0.01500   0.00849  -0.0649   0.1890   1.0000
   9.000   1.3076   0.01543   0.00891  -0.0640   0.1817   1.0000
   9.250   1.3296   0.01576   0.00928  -0.0632   0.1744   1.0000
   9.500   1.3495   0.01621   0.00973  -0.0621   0.1674   1.0000
   9.750   1.3701   0.01660   0.01014  -0.0612   0.1589   1.0000
  10.000   1.3888   0.01704   0.01060  -0.0599   0.1486   1.0000
  10.250   1.4040   0.01761   0.01112  -0.0581   0.1329   1.0000
  10.500   1.4093   0.01880   0.01203  -0.0551   0.0924   1.0000
  10.750   1.4007   0.02094   0.01385  -0.0505   0.0514   1.0000
  11.000   1.4043   0.02243   0.01530  -0.0477   0.0379   1.0000
  11.250   1.4103   0.02382   0.01669  -0.0454   0.0311   1.0000
  11.500   1.4164   0.02526   0.01816  -0.0434   0.0274   1.0000
  11.750   1.4253   0.02654   0.01951  -0.0418   0.0251   1.0000
  12.000   1.4295   0.02825   0.02126  -0.0400   0.0232   1.0000
  12.250   1.4357   0.02986   0.02296  -0.0385   0.0221   1.0000
  12.500   1.4420   0.03152   0.02471  -0.0372   0.0211   1.0000
  12.750   1.4467   0.03338   0.02666  -0.0360   0.0202   1.0000
  13.000   1.4483   0.03560   0.02896  -0.0348   0.0195   1.0000
  13.250   1.4442   0.03847   0.03193  -0.0337   0.0188   1.0000
  13.500   1.4405   0.04144   0.03502  -0.0328   0.0183   1.0000
  13.750   1.4423   0.04394   0.03763  -0.0323   0.0179   1.0000
  14.000   1.4420   0.04677   0.04057  -0.0320   0.0174   1.0000
  14.250   1.4406   0.04979   0.04370  -0.0318   0.0170   1.0000
  14.500   1.4378   0.05308   0.04709  -0.0318   0.0165   1.0000
  14.750   1.4337   0.05665   0.05075  -0.0320   0.0162   1.0000
  15.000   1.4280   0.06050   0.05469  -0.0324   0.0159   1.0000
  15.250   1.4202   0.06469   0.05898  -0.0329   0.0156   1.0000
  15.500   1.4100   0.06931   0.06370  -0.0336   0.0154   1.0000
  15.750   1.3983   0.07417   0.06866  -0.0344   0.0151   1.0000
  16.000   1.3846   0.07928   0.07387  -0.0353   0.0149   1.0000
  16.250   1.3801   0.08338   0.07807  -0.0362   0.0148   1.0000
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