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GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il)
Reynolds number: 500,000
Max Cl/Cd: 113.98 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe311-il-500000.txt
Download as CSV file: xf-goe311-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 311 (MVA H.43) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2618   0.08699   0.08496  -0.0341   0.9491   0.0245
  -7.500  -0.2592   0.08424   0.08220  -0.0349   0.9334   0.0254
  -7.250  -0.2522   0.08009   0.07801  -0.0419   0.9165   0.0273
  -7.000  -0.2384   0.07582   0.07369  -0.0476   0.9011   0.0276
  -6.750  -0.2693   0.02039   0.01646  -0.0848   0.8892   0.0161
  -6.500  -0.2461   0.01774   0.01331  -0.0848   0.8765   0.0166
  -6.250  -0.2218   0.01602   0.01119  -0.0843   0.8623   0.0170
  -6.000  -0.1972   0.01444   0.00929  -0.0839   0.8467   0.0183
  -5.750  -0.1711   0.01378   0.00846  -0.0835   0.8298   0.0198
  -5.500  -0.1445   0.01311   0.00754  -0.0831   0.8123   0.0214
  -5.250  -0.1178   0.01241   0.00663  -0.0827   0.7948   0.0236
  -5.000  -0.0901   0.01218   0.00627  -0.0824   0.7778   0.0268
  -4.750  -0.0620   0.01229   0.00634  -0.0822   0.7618   0.0313
  -4.500  -0.0335   0.01260   0.00659  -0.0821   0.7467   0.0373
  -4.250  -0.0049   0.01321   0.00715  -0.0820   0.7317   0.0427
  -4.000   0.0225   0.01286   0.00661  -0.0820   0.7170   0.0469
  -3.750   0.0502   0.01273   0.00641  -0.0820   0.7014   0.0503
  -3.500   0.0782   0.01263   0.00618  -0.0819   0.6842   0.0534
  -3.250   0.1064   0.01275   0.00615  -0.0819   0.6653   0.0554
  -3.000   0.1337   0.01178   0.00495  -0.0819   0.6468   0.0588
  -2.750   0.1615   0.01148   0.00455  -0.0818   0.6282   0.0616
  -2.500   0.1894   0.01129   0.00423  -0.0818   0.6116   0.0642
  -2.250   0.2174   0.01105   0.00384  -0.0818   0.5984   0.0650
  -2.000   0.2454   0.01084   0.00350  -0.0817   0.5879   0.0655
  -1.750   0.2735   0.01065   0.00322  -0.0817   0.5799   0.0660
  -1.500   0.3015   0.01052   0.00298  -0.0816   0.5733   0.0665
  -1.250   0.3297   0.01039   0.00279  -0.0816   0.5675   0.0671
  -1.000   0.3578   0.01030   0.00264  -0.0816   0.5621   0.0679
  -0.750   0.3858   0.01022   0.00250  -0.0815   0.5577   0.0704
  -0.500   0.4141   0.01013   0.00241  -0.0816   0.5535   0.0737
  -0.250   0.4423   0.01007   0.00236  -0.0816   0.5493   0.0784
   0.000   0.4703   0.01005   0.00240  -0.0816   0.5454   0.0973
   0.250   0.4985   0.01014   0.00248  -0.0816   0.5416   0.1165
   0.500   0.5270   0.01019   0.00255  -0.0817   0.5381   0.1272
   0.750   0.5554   0.01028   0.00260  -0.0818   0.5341   0.1341
   1.000   0.5834   0.01038   0.00268  -0.0818   0.5295   0.1412
   1.250   0.6116   0.01049   0.00276  -0.0819   0.5247   0.1463
   1.500   0.6396   0.01049   0.00279  -0.0819   0.5196   0.1513
   1.750   0.6675   0.01058   0.00287  -0.0820   0.5148   0.1570
   2.000   0.6955   0.01068   0.00294  -0.0820   0.5104   0.1614
   2.250   0.7235   0.01063   0.00296  -0.0821   0.5054   0.1660
   2.500   0.7512   0.01067   0.00299  -0.0821   0.4996   0.1707
   2.750   0.7790   0.01072   0.00306  -0.0821   0.4938   0.1760
   3.000   0.8069   0.01068   0.00309  -0.0822   0.4883   0.1828
   3.250   0.8346   0.01074   0.00315  -0.0822   0.4841   0.1900
   3.500   0.8624   0.01078   0.00327  -0.0823   0.4803   0.2020
   3.750   0.8904   0.01075   0.00337  -0.0824   0.4759   0.2234
   4.000   0.9180   0.01068   0.00350  -0.0825   0.4715   0.2925
   4.250   0.9457   0.00943   0.00363  -0.0826   0.4672   1.0000
   4.500   0.9732   0.00948   0.00373  -0.0826   0.4624   1.0000
   4.750   1.0005   0.00955   0.00382  -0.0826   0.4570   1.0000
   5.000   1.0274   0.00969   0.00392  -0.0825   0.4518   1.0000
   5.250   1.0550   0.00974   0.00404  -0.0825   0.4456   1.0000
   5.500   1.0819   0.00984   0.00414  -0.0824   0.4384   1.0000
   5.750   1.1089   0.00991   0.00423  -0.0823   0.4267   1.0000
   6.000   1.1356   0.01001   0.00433  -0.0822   0.4123   1.0000
   6.250   1.1615   0.01019   0.00447  -0.0820   0.3938   1.0000
   6.500   1.1862   0.01050   0.00466  -0.0817   0.3620   1.0000
   6.750   1.2087   0.01107   0.00502  -0.0811   0.3220   1.0000
   7.000   1.2297   0.01181   0.00552  -0.0803   0.2783   1.0000
   7.250   1.2501   0.01259   0.00609  -0.0795   0.2372   1.0000
   7.500   1.2695   0.01346   0.00673  -0.0786   0.1963   1.0000
   7.750   1.2864   0.01452   0.00750  -0.0773   0.1506   1.0000
   8.000   1.2964   0.01614   0.00867  -0.0751   0.0823   1.0000
   8.250   1.3139   0.01699   0.00946  -0.0738   0.0598   1.0000
   8.500   1.3230   0.01848   0.01070  -0.0713   0.0225   1.0000
   8.750   1.3397   0.01925   0.01155  -0.0698   0.0193   1.0000
   9.000   1.3557   0.02001   0.01241  -0.0682   0.0177   1.0000
   9.250   1.3681   0.02090   0.01339  -0.0661   0.0166   1.0000
   9.500   1.3747   0.02201   0.01459  -0.0632   0.0156   1.0000
   9.750   1.3769   0.02349   0.01620  -0.0601   0.0148   1.0000
  10.000   1.3800   0.02505   0.01789  -0.0574   0.0144   1.0000
  10.250   1.3869   0.02645   0.01938  -0.0555   0.0141   1.0000
  10.500   1.3921   0.02807   0.02110  -0.0537   0.0137   1.0000
  10.750   1.3962   0.02991   0.02303  -0.0521   0.0132   1.0000
  11.000   1.3993   0.03196   0.02518  -0.0508   0.0127   1.0000
  11.250   1.4014   0.03425   0.02757  -0.0497   0.0122   1.0000
  11.500   1.4018   0.03683   0.03024  -0.0488   0.0119   1.0000
  11.750   1.4006   0.03965   0.03315  -0.0480   0.0116   1.0000
  12.000   1.3982   0.04267   0.03626  -0.0473   0.0114   1.0000
  12.250   1.3943   0.04586   0.03953  -0.0466   0.0112   1.0000
  12.500   1.3892   0.04919   0.04295  -0.0458   0.0110   1.0000
  12.750   1.3837   0.05246   0.04628  -0.0448   0.0108   1.0000
  13.000   1.3798   0.05536   0.04924  -0.0431   0.0106   1.0000
  13.250   1.3816   0.05771   0.05165  -0.0415   0.0104   1.0000
  13.500   1.3855   0.06023   0.05428  -0.0413   0.0103   1.0000
  13.750   1.3893   0.06271   0.05687  -0.0408   0.0102   1.0000
  14.000   1.3932   0.06519   0.05945  -0.0401   0.0100   1.0000
  14.250   1.3966   0.06773   0.06209  -0.0395   0.0099   1.0000
  14.500   1.3993   0.07044   0.06492  -0.0391   0.0097   1.0000
  14.750   1.4010   0.07335   0.06795  -0.0390   0.0095   1.0000
  15.000   1.4021   0.07639   0.07113  -0.0389   0.0093   1.0000
  15.250   1.4021   0.07963   0.07449  -0.0390   0.0090   1.0000
  15.500   1.4016   0.08293   0.07791  -0.0391   0.0089   1.0000
  15.750   1.4000   0.08645   0.08157  -0.0392   0.0088   1.0000
  16.000   1.3969   0.09027   0.08554  -0.0395   0.0087   1.0000
  16.250   1.3922   0.09440   0.08983  -0.0401   0.0087   1.0000
  16.500   1.3855   0.09894   0.09454  -0.0410   0.0087   1.0000
  16.750   1.3767   0.10396   0.09974  -0.0422   0.0088   1.0000
  17.000   1.3667   0.10933   0.10529  -0.0439   0.0088   1.0000
  17.250   1.3551   0.11512   0.11126  -0.0459   0.0089   1.0000
  17.500   1.3420   0.12133   0.11766  -0.0484   0.0090   1.0000
  17.750   1.3285   0.12790   0.12441  -0.0515   0.0091   1.0000
  18.000   1.3135   0.13501   0.13170  -0.0551   0.0093   1.0000
  18.250   1.2985   0.14245   0.13931  -0.0592   0.0094   1.0000
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