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GOE 451 AIRFOIL (modified line 6) (goe451-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 451 AIRFOIL (modified line 6) (goe451-il)
Reynolds number: 200,000
Max Cl/Cd: 50.73 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe451-il-200000.txt
Download as CSV file: xf-goe451-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 451 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4133   0.09402   0.09065  -0.0277   1.0000   0.0175
  -7.000  -0.4101   0.08910   0.08577  -0.0255   1.0000   0.0181
  -6.750  -0.4040   0.08561   0.08231  -0.0257   0.9997   0.0185
  -6.500  -0.3912   0.08188   0.07859  -0.0283   0.9975   0.0191
  -6.250  -0.3777   0.07836   0.07509  -0.0312   0.9955   0.0199
  -6.000  -0.3625   0.07479   0.07153  -0.0346   0.9938   0.0207
  -5.750  -0.3460   0.07132   0.06807  -0.0381   0.9926   0.0216
  -5.500  -0.3273   0.06773   0.06442  -0.0420   0.9915   0.0227
  -5.250  -0.3018   0.06425   0.06091  -0.0472   0.9900   0.0264
  -5.000  -0.2411   0.06227   0.05873  -0.0608   0.9877   0.0289
  -4.750  -0.2108   0.05830   0.05468  -0.0654   0.9863   0.0290
  -4.500  -0.1740   0.05385   0.05010  -0.0711   0.9833   0.0291
  -4.250  -0.1325   0.04910   0.04518  -0.0773   0.9764   0.0292
  -4.000  -0.0956   0.04118   0.03719  -0.0844   0.9680   0.0301
  -3.750  -0.0507   0.03594   0.03178  -0.0910   0.9361   0.0312
  -3.500   0.0223   0.03027   0.02534  -0.1027   0.8090   0.0328
  -3.250   0.0492   0.02795   0.02218  -0.1032   0.6879   0.0339
  -3.000   0.0601   0.02842   0.02040  -0.1009   0.0631   0.0347
  -2.750   0.0910   0.02572   0.01736  -0.1020   0.0499   0.0356
  -2.250   0.1537   0.02056   0.01124  -0.1026   0.0358   0.0258
  -2.000   0.1818   0.01890   0.00927  -0.1025   0.0313   0.0252
  -1.750   0.2106   0.01764   0.00752  -0.1023   0.0301   0.0276
  -1.500   0.2369   0.01610   0.00571  -0.1025   0.0245   0.0449
  -1.250   0.2618   0.01536   0.00496  -0.1027   0.0218   0.0682
  -1.000   0.2873   0.01465   0.00424  -0.1025   0.0193   0.0652
  -0.750   0.3107   0.01462   0.00426  -0.1021   0.0154   0.0636
  -0.500   0.3364   0.01426   0.00387  -0.1021   0.0129   0.0631
  -0.250   0.3602   0.01439   0.00395  -0.1019   0.0120   0.0640
   0.000   0.3821   0.01491   0.00434  -0.1014   0.0113   0.0667
   0.750   0.4480   0.01787   0.00720  -0.1006   0.0106   0.2730
   1.000   0.4657   0.01666   0.00743  -0.0989   0.0106   1.0000
   1.250   0.4899   0.01702   0.00771  -0.0990   0.0105   1.0000
   1.500   0.5140   0.01740   0.00802  -0.0990   0.0105   1.0000
   1.750   0.5380   0.01780   0.00837  -0.0990   0.0105   1.0000
   2.000   0.5619   0.01813   0.00866  -0.0991   0.0104   1.0000
   2.250   0.5855   0.01788   0.00848  -0.0989   0.0101   1.0000
   2.500   0.6095   0.01823   0.00882  -0.0988   0.0088   1.0000
   2.750   0.6341   0.01938   0.01001  -0.0988   0.0083   1.0000
   3.000   0.6591   0.02105   0.01158  -0.0991   0.0078   1.0000
   3.250   0.6850   0.02486   0.01519  -0.0999   0.0075   1.0000
   3.750   0.7118   0.01403   0.00500  -0.0947   0.0072   1.0000
   4.000   0.7351   0.01454   0.00570  -0.0942   0.0071   1.0000
   4.250   0.7580   0.01520   0.00655  -0.0936   0.0071   1.0000
   4.500   0.7805   0.01604   0.00759  -0.0930   0.0070   1.0000
   4.750   0.8025   0.01696   0.00874  -0.0924   0.0069   1.0000
   5.000   0.8241   0.01829   0.01047  -0.0916   0.0067   1.0000
   5.250   0.8452   0.01972   0.01220  -0.0909   0.0065   1.0000
   5.500   0.8653   0.02149   0.01431  -0.0901   0.0061   1.0000
   5.750   0.8840   0.02360   0.01687  -0.0894   0.0058   1.0000
   6.000   0.9083   0.02746   0.02012  -0.0903   0.0055   0.1770
   6.250   0.9229   0.03053   0.02385  -0.0898   0.0052   0.2214
   6.500   0.9345   0.03425   0.02826  -0.0893   0.0050   0.2862
   6.750   0.9443   0.03905   0.03342  -0.0884   0.0049   0.2717
   7.000   0.9524   0.04438   0.03904  -0.0872   0.0047   0.2399
   7.250   0.9587   0.05075   0.04556  -0.0858   0.0046   0.1774
   8.500   1.0757   0.07586   0.07058  -0.0875   0.0044   1.0000
   8.750   1.0838   0.07696   0.07205  -0.0854   0.0044   1.0000
   9.000   1.0913   0.07842   0.07383  -0.0834   0.0043   1.0000
   9.250   1.0977   0.08032   0.07603  -0.0815   0.0043   1.0000
   9.500   1.1024   0.08272   0.07868  -0.0797   0.0043   1.0000
   9.750   1.1050   0.08554   0.08171  -0.0782   0.0042   1.0000
  10.000   1.1045   0.08873   0.08510  -0.0767   0.0042   1.0000
  10.250   1.1011   0.09211   0.08865  -0.0754   0.0041   1.0000
  10.500   1.0941   0.09566   0.09235  -0.0742   0.0041   1.0000
  10.750   1.0814   0.09897   0.09578  -0.0725   0.0041   1.0000
  11.000   1.0663   0.10259   0.09950  -0.0716   0.0041   1.0000
  11.250   1.0514   0.10683   0.10383  -0.0722   0.0041   1.0000
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