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GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 29B AIRFOIL (goe29b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.14 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe29b-il-1000000.txt
Download as CSV file: xf-goe29b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 29B 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2373   0.10520   0.10322  -0.0178   0.8523   0.0223
  -8.750  -0.2329   0.10187   0.09982  -0.0208   0.8350   0.0225
  -8.500  -0.2281   0.09869   0.09657  -0.0234   0.8173   0.0226
  -8.250  -0.2209   0.09515   0.09296  -0.0244   0.7983   0.0227
  -8.000  -0.2102   0.09256   0.09030  -0.0246   0.7765   0.0228
  -7.750  -0.1123   0.07938   0.07683  -0.0315   0.6752   0.0234
  -7.250  -0.0963   0.07403   0.07139  -0.0334   0.6498   0.0243
  -7.000  -0.0888   0.07117   0.06848  -0.0346   0.6403   0.0249
  -6.500  -0.1364   0.07808   0.07531  -0.0357   0.6485   0.0250
  -6.250  -0.1099   0.07307   0.07023  -0.0471   0.6399   0.0261
  -6.000  -0.0855   0.06901   0.06611  -0.0540   0.6318   0.0262
  -5.750  -0.0710   0.06561   0.06266  -0.0550   0.6235   0.0264
  -5.500  -0.0518   0.06337   0.06040  -0.0565   0.6163   0.0266
  -5.250  -0.0301   0.06113   0.05811  -0.0590   0.6090   0.0268
  -5.000  -0.0061   0.05872   0.05566  -0.0621   0.6026   0.0272
  -4.750   0.0197   0.05617   0.05306  -0.0656   0.5958   0.0277
  -4.500   0.0475   0.05342   0.05024  -0.0696   0.5887   0.0286
  -4.250   0.0985   0.04779   0.04443  -0.0812   0.5835   0.0300
  -2.500   0.3089   0.02955   0.02543  -0.0987   0.5267   0.0348
  -2.250   0.3363   0.02837   0.02416  -0.0995   0.5159   0.0351
  -2.000   0.3867   0.01120   0.00518  -0.1068   0.5124   0.0350
  -1.750   0.4154   0.01115   0.00508  -0.1068   0.5006   0.0356
  -1.500   0.4440   0.01113   0.00500  -0.1068   0.4886   0.0362
  -1.250   0.4728   0.01083   0.00457  -0.1068   0.4773   0.0370
  -1.000   0.5014   0.01054   0.00414  -0.1067   0.4670   0.0380
  -0.750   0.5301   0.01031   0.00381  -0.1067   0.4587   0.0388
  -0.500   0.5587   0.00995   0.00335  -0.1067   0.4511   0.0400
  -0.250   0.5874   0.00994   0.00333  -0.1067   0.4444   0.0410
   0.000   0.6159   0.00996   0.00330  -0.1066   0.4367   0.0422
   0.250   0.6446   0.00990   0.00319  -0.1065   0.4307   0.0436
   0.500   0.6731   0.00976   0.00300  -0.1065   0.4243   0.0452
   0.750   0.7015   0.00982   0.00305  -0.1064   0.4181   0.0465
   1.000   0.7302   0.00981   0.00305  -0.1064   0.4133   0.0482
   1.250   0.7587   0.00982   0.00302  -0.1063   0.4077   0.0498
   1.500   0.7870   0.00974   0.00290  -0.1063   0.4013   0.0518
   1.750   0.8156   0.00979   0.00297  -0.1063   0.3951   0.0536
   2.000   0.8437   0.00988   0.00301  -0.1062   0.3869   0.0557
   2.250   0.8721   0.00994   0.00305  -0.1061   0.3798   0.0571
   2.500   0.9002   0.00984   0.00293  -0.1061   0.3699   0.0596
   2.750   0.9283   0.00992   0.00299  -0.1061   0.3584   0.0618
   3.000   0.9561   0.01003   0.00304  -0.1060   0.3422   0.0639
   3.250   0.9830   0.01025   0.00312  -0.1058   0.3150   0.0654
   3.500   1.0086   0.01057   0.00323  -0.1056   0.2747   0.0683
   3.750   1.0351   0.01085   0.00341  -0.1053   0.2556   0.0704
   4.000   1.0620   0.01105   0.00356  -0.1052   0.2460   0.0726
   4.250   1.0892   0.01122   0.00371  -0.1050   0.2399   0.0742
   4.500   1.1167   0.01128   0.00376  -0.1050   0.2357   0.0776
   4.750   1.1437   0.01145   0.00391  -0.1048   0.2312   0.0805
   5.000   1.1704   0.01165   0.00409  -0.1046   0.2263   0.0836
   5.250   1.1979   0.01174   0.00420  -0.1045   0.2245   0.0870
   5.500   1.2252   0.01185   0.00435  -0.1044   0.2226   0.0926
   5.750   1.2522   0.01199   0.00451  -0.1043   0.2205   0.1016
   6.000   1.2758   0.01087   0.00493  -0.1039   0.2185   1.0000
   6.250   1.3023   0.01111   0.00513  -0.1037   0.2160   1.0000
   6.500   1.3283   0.01138   0.00537  -0.1034   0.2128   1.0000
   6.750   1.3543   0.01165   0.00562  -0.1031   0.2103   1.0000
   7.000   1.3812   0.01178   0.00577  -0.1030   0.2089   1.0000
   7.250   1.4079   0.01194   0.00594  -0.1028   0.2067   1.0000
   7.500   1.4342   0.01214   0.00614  -0.1026   0.2045   1.0000
   7.750   1.4599   0.01238   0.00637  -0.1024   0.2014   1.0000
   8.000   1.4849   0.01268   0.00665  -0.1020   0.1977   1.0000
   8.250   1.5099   0.01298   0.00695  -0.1017   0.1946   1.0000
   8.500   1.5362   0.01312   0.00712  -0.1015   0.1931   1.0000
   8.750   1.5622   0.01329   0.00732  -0.1013   0.1905   1.0000
   9.000   1.5874   0.01352   0.00754  -0.1010   0.1866   1.0000
   9.250   1.6113   0.01386   0.00784  -0.1005   0.1812   1.0000
   9.500   1.6365   0.01406   0.00808  -0.1002   0.1775   1.0000
   9.750   1.6609   0.01432   0.00832  -0.0999   0.1709   1.0000
  10.000   1.6840   0.01469   0.00864  -0.0993   0.1621   1.0000
  10.250   1.7042   0.01528   0.00910  -0.0984   0.1435   1.0000
  10.500   1.7206   0.01613   0.00981  -0.0970   0.1255   1.0000
  11.000   1.7543   0.01759   0.01117  -0.0943   0.1076   1.0000
  11.250   1.7705   0.01828   0.01185  -0.0929   0.1002   1.0000
  11.500   1.7821   0.01916   0.01267  -0.0907   0.0903   1.0000
  11.750   1.7792   0.02071   0.01404  -0.0867   0.0672   1.0000
  12.000   1.7523   0.02414   0.01726  -0.0810   0.0294   1.0000
  12.250   1.7467   0.02652   0.01964  -0.0783   0.0187   1.0000
  12.500   1.7524   0.02817   0.02135  -0.0769   0.0171   1.0000
  12.750   1.7565   0.03005   0.02330  -0.0756   0.0160   1.0000
  13.000   1.7607   0.03204   0.02536  -0.0745   0.0152   1.0000
  13.250   1.7657   0.03402   0.02742  -0.0737   0.0148   1.0000
  13.500   1.7692   0.03625   0.02973  -0.0730   0.0144   1.0000
  13.750   1.7707   0.03878   0.03235  -0.0724   0.0140   1.0000
  14.000   1.7701   0.04164   0.03529  -0.0720   0.0136   1.0000
  14.250   1.7673   0.04486   0.03861  -0.0718   0.0133   1.0000
  14.500   1.7614   0.04850   0.04236  -0.0717   0.0129   1.0000
  14.750   1.7522   0.05258   0.04656  -0.0717   0.0127   1.0000
  15.000   1.7466   0.05626   0.05034  -0.0717   0.0125   1.0000
  15.250   1.7409   0.06003   0.05421  -0.0719   0.0124   1.0000
  15.500   1.7338   0.06408   0.05836  -0.0722   0.0122   1.0000
  15.750   1.7256   0.06836   0.06274  -0.0727   0.0121   1.0000
  16.000   1.7159   0.07291   0.06740  -0.0733   0.0119   1.0000
  16.250   1.7051   0.07775   0.07235  -0.0741   0.0118   1.0000
  16.500   1.6933   0.08282   0.07753  -0.0750   0.0116   1.0000
  16.750   1.6806   0.08808   0.08289  -0.0761   0.0115   1.0000
  17.000   1.6670   0.09356   0.08848  -0.0773   0.0114   1.0000
  17.250   1.6529   0.09920   0.09424  -0.0787   0.0113   1.0000
  17.500   1.6375   0.10507   0.10022  -0.0803   0.0112   1.0000
  17.750   1.6218   0.11110   0.10636  -0.0820   0.0111   1.0000
  18.000   1.6056   0.11733   0.11271  -0.0840   0.0110   1.0000
  18.250   1.5891   0.12368   0.11917  -0.0861   0.0109   1.0000
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