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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 100,000
Max Cl/Cd: 60.03 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe529-il-100000-n5.txt
Download as CSV file: xf-goe529-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2493   0.11129   0.10666  -0.0400   1.0000   0.0468
  -9.000  -0.2584   0.11026   0.10574  -0.0401   1.0000   0.0471
  -8.750  -0.2706   0.10937   0.10499  -0.0391   1.0000   0.0472
  -8.500  -0.2606   0.10597   0.10162  -0.0443   0.9906   0.0473
  -8.250  -0.2359   0.09920   0.09484  -0.0420   0.9895   0.0487
  -8.000  -0.2157   0.09513   0.09076  -0.0449   0.9809   0.0502
  -7.750  -0.1975   0.09137   0.08698  -0.0490   0.9700   0.0519
  -7.500  -0.1803   0.08787   0.08348  -0.0541   0.9575   0.0553
  -7.250  -0.1606   0.08444   0.08001  -0.0709   0.9361   0.0586
  -7.000  -0.1372   0.07988   0.07537  -0.0797   0.9217   0.0588
  -6.750  -0.1225   0.07487   0.07038  -0.0794   0.9115   0.0595
  -6.250  -0.0782   0.06372   0.05897  -0.0905   0.8863   0.0471
  -5.750  -0.0345   0.05493   0.04987  -0.0987   0.8615   0.0470
  -5.500  -0.0142   0.05121   0.04602  -0.1010   0.8490   0.0465
  -5.250   0.0080   0.04719   0.04179  -0.1043   0.8369   0.0484
  -5.000   0.0291   0.04595   0.04048  -0.1043   0.8262   0.0511
  -4.750   0.0549   0.04149   0.03568  -0.1076   0.8160   0.0504
  -4.500   0.0794   0.03736   0.03118  -0.1097   0.8046   0.0501
  -4.250   0.1040   0.03518   0.02874  -0.1105   0.7939   0.0523
  -4.000   0.1305   0.03216   0.02529  -0.1115   0.7845   0.0539
  -3.750   0.1552   0.02925   0.02194  -0.1119   0.7737   0.0540
  -3.500   0.1812   0.02679   0.01896  -0.1121   0.7645   0.0545
  -3.250   0.2078   0.02480   0.01648  -0.1121   0.7560   0.0557
  -3.000   0.2345   0.02334   0.01448  -0.1118   0.7473   0.0583
  -2.750   0.2618   0.02202   0.01279  -0.1116   0.7400   0.0593
  -2.500   0.2876   0.02102   0.01159  -0.1113   0.7315   0.0604
  -2.250   0.3150   0.02022   0.01059  -0.1111   0.7247   0.0618
  -2.000   0.3412   0.01958   0.00981  -0.1107   0.7166   0.0637
  -1.750   0.3686   0.01896   0.00901  -0.1103   0.7099   0.0661
  -1.500   0.3948   0.01850   0.00841  -0.1099   0.7023   0.0698
  -1.250   0.4216   0.01808   0.00792  -0.1096   0.6956   0.0753
  -1.000   0.4476   0.01774   0.00754  -0.1091   0.6884   0.0813
  -0.750   0.4740   0.01735   0.00707  -0.1086   0.6817   0.0890
  -0.500   0.5002   0.01708   0.00678  -0.1081   0.6749   0.1024
  -0.250   0.5268   0.01688   0.00660  -0.1078   0.6678   0.1223
   0.000   0.5535   0.01677   0.00651  -0.1075   0.6614   0.1542
   0.250   0.5797   0.01664   0.00650  -0.1072   0.6541   0.2012
   0.500   0.6069   0.01636   0.00638  -0.1071   0.6481   0.2728
   1.000   0.6739   0.01498   0.00629  -0.1091   0.6339   1.0000
   1.250   0.6986   0.01519   0.00638  -0.1084   0.6260   1.0000
   1.500   0.7250   0.01537   0.00638  -0.1080   0.6193   1.0000
   1.750   0.7497   0.01560   0.00652  -0.1074   0.6115   1.0000
   2.000   0.7757   0.01579   0.00658  -0.1069   0.6045   1.0000
   2.250   0.8002   0.01601   0.00674  -0.1063   0.5964   1.0000
   2.500   0.8259   0.01620   0.00684  -0.1058   0.5891   1.0000
   2.750   0.8501   0.01643   0.00704  -0.1051   0.5806   1.0000
   3.000   0.8758   0.01662   0.00714  -0.1046   0.5731   1.0000
   3.250   0.8994   0.01685   0.00739  -0.1038   0.5639   1.0000
   3.500   0.9249   0.01702   0.00748  -0.1033   0.5565   1.0000
   3.750   0.9481   0.01726   0.00775  -0.1025   0.5467   1.0000
   4.000   0.9726   0.01746   0.00795  -0.1019   0.5385   1.0000
   4.250   0.9966   0.01768   0.00817  -0.1012   0.5298   1.0000
   4.500   1.0203   0.01792   0.00843  -0.1005   0.5212   1.0000
   5.000   1.0677   0.01840   0.00897  -0.0990   0.5040   1.0000
   5.250   1.0915   0.01861   0.00917  -0.0983   0.4954   1.0000
   5.500   1.1145   0.01888   0.00948  -0.0974   0.4862   1.0000
   5.750   1.1375   0.01917   0.00982  -0.0966   0.4772   1.0000
   6.000   1.1609   0.01941   0.01006  -0.0958   0.4689   1.0000
   6.250   1.1827   0.01976   0.01048  -0.0949   0.4590   1.0000
   6.500   1.2055   0.02008   0.01084  -0.0941   0.4507   1.0000
   6.750   1.2274   0.02045   0.01127  -0.0931   0.4420   1.0000
   7.000   1.2493   0.02084   0.01173  -0.0922   0.4337   1.0000
   7.250   1.2712   0.02122   0.01215  -0.0913   0.4252   1.0000
   7.500   1.2916   0.02168   0.01274  -0.0902   0.4159   1.0000
   7.750   1.3132   0.02209   0.01318  -0.0892   0.4079   1.0000
   8.000   1.3326   0.02259   0.01385  -0.0880   0.3991   1.0000
   8.250   1.3536   0.02306   0.01440  -0.0870   0.3917   1.0000
   8.500   1.3708   0.02355   0.01499  -0.0854   0.3805   1.0000
   8.750   1.3839   0.02403   0.01553  -0.0832   0.3642   1.0000
   9.000   1.3936   0.02459   0.01617  -0.0805   0.3457   1.0000
   9.250   1.4033   0.02521   0.01687  -0.0779   0.3291   1.0000
   9.500   1.4108   0.02590   0.01762  -0.0750   0.3134   1.0000
   9.750   1.4154   0.02672   0.01848  -0.0718   0.2958   1.0000
  10.000   1.4172   0.02777   0.01949  -0.0686   0.2762   1.0000
  10.250   1.4195   0.02897   0.02071  -0.0657   0.2566   1.0000
  10.500   1.4183   0.03049   0.02224  -0.0628   0.2347   1.0000
  10.750   1.4155   0.03230   0.02402  -0.0601   0.2113   1.0000
  11.000   1.4081   0.03465   0.02627  -0.0576   0.1786   1.0000
  11.250   1.3928   0.03790   0.02927  -0.0552   0.1421   1.0000
  11.500   1.3780   0.04149   0.03268  -0.0535   0.1222   1.0000
  11.750   1.3662   0.04511   0.03625  -0.0522   0.1037   1.0000
  12.000   1.3543   0.04898   0.04007  -0.0514   0.0679   1.0000
  12.250   1.3376   0.05358   0.04452  -0.0510   0.0538   1.0000
  12.500   1.3259   0.05782   0.04878  -0.0508   0.0446   1.0000
  12.750   1.3151   0.06214   0.05317  -0.0508   0.0374   1.0000
  13.000   1.3059   0.06644   0.05756  -0.0510   0.0327   1.0000
  13.250   1.2971   0.07085   0.06206  -0.0515   0.0301   1.0000
  13.500   1.2894   0.07527   0.06662  -0.0521   0.0282   1.0000
  13.750   1.2820   0.07982   0.07131  -0.0529   0.0270   1.0000
  14.000   1.2734   0.08468   0.07629  -0.0540   0.0258   1.0000
  14.250   1.2646   0.08971   0.08145  -0.0553   0.0250   1.0000
  14.500   1.2563   0.09481   0.08665  -0.0567   0.0244   1.0000
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