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GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 654 AIRFOIL (goe654-il)
Reynolds number: 100,000
Max Cl/Cd: 49.97 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe654-il-100000-n5.txt
Download as CSV file: xf-goe654-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 654 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  -0.1954   0.10171   0.09718  -0.0472   0.9785   0.0809
  -9.000  -0.2013   0.09742   0.09293  -0.0586   0.9572   0.0839
  -8.750  -0.1948   0.09241   0.08792  -0.0672   0.9390   0.0842
  -8.500  -0.1789   0.08701   0.08251  -0.0730   0.9250   0.0844
  -8.000  -0.1590   0.06775   0.06300  -0.0878   0.8962   0.0533
  -7.750  -0.1441   0.06315   0.05830  -0.0925   0.8796   0.0529
  -7.500  -0.1319   0.05896   0.05399  -0.0961   0.8626   0.0523
  -7.250  -0.1239   0.05463   0.04948  -0.0991   0.8454   0.0514
  -7.000  -0.1187   0.05002   0.04462  -0.1015   0.8290   0.0504
  -6.750  -0.1138   0.04547   0.03973  -0.1030   0.8136   0.0495
  -6.500  -0.1063   0.04131   0.03513  -0.1035   0.7994   0.0488
  -6.250  -0.0944   0.03782   0.03117  -0.1035   0.7865   0.0483
  -6.000  -0.0770   0.03533   0.02828  -0.1033   0.7746   0.0487
  -5.750  -0.0588   0.03333   0.02592  -0.1026   0.7616   0.0496
  -5.500  -0.0394   0.03143   0.02363  -0.1019   0.7492   0.0502
  -5.250  -0.0178   0.02963   0.02143  -0.1013   0.7382   0.0503
  -5.000   0.0045   0.02807   0.01949  -0.1005   0.7272   0.0504
  -4.750   0.0276   0.02672   0.01782  -0.0998   0.7164   0.0506
  -4.250   0.0768   0.02451   0.01503  -0.0984   0.6963   0.0513
  -4.000   0.1024   0.02361   0.01388  -0.0979   0.6872   0.0518
  -3.750   0.1276   0.02288   0.01292  -0.0971   0.6768   0.0528
  -3.500   0.1523   0.02217   0.01209  -0.0964   0.6657   0.0541
  -3.250   0.1774   0.02156   0.01140  -0.0958   0.6553   0.0556
  -3.000   0.2017   0.02103   0.01080  -0.0949   0.6440   0.0567
  -2.750   0.2266   0.02053   0.01020  -0.0942   0.6346   0.0578
  -2.500   0.2515   0.02010   0.00969  -0.0934   0.6264   0.0590
  -2.250   0.2763   0.01974   0.00924  -0.0927   0.6187   0.0605
  -2.000   0.3011   0.01944   0.00884  -0.0919   0.6108   0.0621
  -1.750   0.3260   0.01912   0.00847  -0.0913   0.6039   0.0648
  -1.500   0.3509   0.01892   0.00822  -0.0906   0.5962   0.0696
  -1.000   0.4014   0.01848   0.00771  -0.0894   0.5822   0.0867
  -0.750   0.4266   0.01809   0.00746  -0.0888   0.5756   0.1292
  -0.500   0.4505   0.01737   0.00742  -0.0884   0.5689   0.3156
  -0.250   0.4722   0.01680   0.00755  -0.0872   0.5617   0.5321
   0.000   0.5413   0.01584   0.00759  -0.0939   0.5532   0.9707
   0.250   0.5780   0.01601   0.00756  -0.0958   0.5452   1.0000
   0.500   0.6021   0.01618   0.00749  -0.0950   0.5393   1.0000
   0.750   0.6239   0.01638   0.00759  -0.0939   0.5315   1.0000
   1.000   0.6474   0.01657   0.00760  -0.0930   0.5246   1.0000
   1.250   0.6705   0.01678   0.00767  -0.0921   0.5175   1.0000
   1.500   0.6934   0.01699   0.00776  -0.0911   0.5098   1.0000
   1.750   0.7176   0.01720   0.00781  -0.0903   0.5035   1.0000
   2.000   0.7397   0.01744   0.00800  -0.0893   0.4955   1.0000
   2.250   0.7637   0.01765   0.00807  -0.0885   0.4887   1.0000
   2.500   0.7859   0.01789   0.00827  -0.0875   0.4806   1.0000
   2.750   0.8091   0.01811   0.00839  -0.0866   0.4731   1.0000
   3.000   0.8317   0.01836   0.00858  -0.0856   0.4653   1.0000
   3.250   0.8543   0.01860   0.00876  -0.0847   0.4576   1.0000
   3.500   0.8773   0.01886   0.00895  -0.0838   0.4508   1.0000
   3.750   0.8994   0.01913   0.00919  -0.0828   0.4429   1.0000
   4.000   0.9225   0.01938   0.00935  -0.0820   0.4364   1.0000
   4.250   0.9439   0.01968   0.00966  -0.0809   0.4283   1.0000
   4.500   0.9669   0.01994   0.00981  -0.0801   0.4223   1.0000
   4.750   0.9881   0.02029   0.01019  -0.0790   0.4148   1.0000
   5.000   1.0104   0.02059   0.01044  -0.0781   0.4089   1.0000
   5.250   1.0322   0.02094   0.01075  -0.0772   0.4028   1.0000
   5.500   1.0533   0.02130   0.01112  -0.0762   0.3964   1.0000
   5.750   1.0757   0.02161   0.01135  -0.0753   0.3914   1.0000
   6.000   1.0960   0.02205   0.01182  -0.0742   0.3854   1.0000
   6.250   1.1169   0.02245   0.01222  -0.0732   0.3800   1.0000
   6.500   1.1394   0.02280   0.01249  -0.0724   0.3756   1.0000
   6.750   1.1584   0.02331   0.01306  -0.0712   0.3700   1.0000
   7.000   1.1783   0.02376   0.01354  -0.0701   0.3649   1.0000
   7.250   1.2001   0.02417   0.01389  -0.0693   0.3607   1.0000
   7.500   1.2187   0.02471   0.01448  -0.0680   0.3558   1.0000
   7.750   1.2366   0.02524   0.01507  -0.0667   0.3507   1.0000
   8.000   1.2568   0.02571   0.01553  -0.0657   0.3463   1.0000
   8.250   1.2766   0.02624   0.01605  -0.0647   0.3420   1.0000
   8.500   1.2908   0.02688   0.01680  -0.0629   0.3369   1.0000
   8.750   1.3077   0.02743   0.01739  -0.0615   0.3322   1.0000
   9.000   1.3292   0.02790   0.01781  -0.0608   0.3281   1.0000
   9.250   1.3386   0.02864   0.01868  -0.0583   0.3235   1.0000
   9.500   1.3496   0.02933   0.01947  -0.0562   0.3187   1.0000
   9.750   1.3656   0.02992   0.02009  -0.0547   0.3144   1.0000
  10.000   1.3839   0.03054   0.02071  -0.0537   0.3105   1.0000
  10.250   1.3881   0.03152   0.02187  -0.0510   0.3060   1.0000
  10.500   1.3978   0.03238   0.02283  -0.0490   0.3016   1.0000
  10.750   1.4134   0.03306   0.02353  -0.0478   0.2976   1.0000
  11.000   1.4243   0.03394   0.02449  -0.0462   0.2934   1.0000
  11.250   1.4238   0.03530   0.02604  -0.0436   0.2887   1.0000
  11.500   1.4294   0.03636   0.02717  -0.0417   0.2835   1.0000
  11.750   1.4395   0.03720   0.02801  -0.0403   0.2783   1.0000
  12.000   1.4306   0.03926   0.03029  -0.0379   0.2728   1.0000
  12.250   1.4315   0.04076   0.03188  -0.0363   0.2670   1.0000
  12.500   1.4345   0.04226   0.03343  -0.0349   0.2619   1.0000
  12.750   1.4234   0.04503   0.03642  -0.0335   0.2562   1.0000
  13.000   1.4233   0.04700   0.03846  -0.0325   0.2510   1.0000
  13.250   1.4212   0.04930   0.04085  -0.0317   0.2461   1.0000
  13.500   1.4072   0.05301   0.04477  -0.0312   0.2408   1.0000
  13.750   1.4041   0.05563   0.04746  -0.0308   0.2356   1.0000
  14.000   1.3933   0.05933   0.05129  -0.0308   0.2303   1.0000
  14.250   1.3737   0.06439   0.05653  -0.0313   0.2250   1.0000
  14.500   1.3769   0.06653   0.05868  -0.0313   0.2191   1.0000
  14.750   1.3426   0.07414   0.06652  -0.0330   0.2140   1.0000
  15.000   1.3237   0.07984   0.07236  -0.0343   0.2086   1.0000
  15.250   1.3202   0.08333   0.07589  -0.0350   0.2034   1.0000
  15.500   1.2695   0.09456   0.08733  -0.0385   0.1982   1.0000
  15.750   1.2761   0.09666   0.08948  -0.0389   0.1928   1.0000
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