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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.88 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe133-il-1000000.txt
Download as CSV file: xf-goe133-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4012   0.09565   0.09404  -0.0166   1.0000   0.0122
  -8.500  -0.3967   0.09195   0.09036  -0.0187   1.0000   0.0122
  -8.250  -0.3967   0.08772   0.08615  -0.0199   1.0000   0.0125
  -8.000  -0.3904   0.08510   0.08355  -0.0209   1.0000   0.0127
  -7.750  -0.3866   0.08253   0.08100  -0.0219   1.0000   0.0128
  -7.500  -0.3837   0.07983   0.07834  -0.0232   1.0000   0.0130
  -7.250  -0.3821   0.07714   0.07567  -0.0244   0.9996   0.0131
  -7.000  -0.3653   0.01724   0.01378  -0.0791   0.9864   0.0115
  -6.750  -0.3329   0.01513   0.01130  -0.0808   0.9844   0.0119
  -6.500  -0.3030   0.01397   0.00991  -0.0815   0.9808   0.0121
  -6.250  -0.2753   0.01198   0.00756  -0.0819   0.9763   0.0129
  -6.000  -0.2452   0.01140   0.00691  -0.0824   0.9725   0.0135
  -5.750  -0.2168   0.01104   0.00648  -0.0824   0.9673   0.0143
  -5.500  -0.1900   0.01064   0.00600  -0.0820   0.9606   0.0151
  -5.250  -0.1627   0.01030   0.00557  -0.0817   0.9545   0.0157
  -5.000  -0.1372   0.00944   0.00459  -0.0811   0.9468   0.0169
  -4.750  -0.1105   0.00919   0.00429  -0.0806   0.9399   0.0180
  -4.500  -0.0838   0.00893   0.00398  -0.0802   0.9311   0.0192
  -4.250  -0.0572   0.00853   0.00350  -0.0797   0.9221   0.0207
  -4.000  -0.0305   0.00838   0.00334  -0.0792   0.9118   0.0227
  -3.750  -0.0032   0.00832   0.00324  -0.0788   0.9000   0.0246
  -3.500   0.0239   0.00802   0.00291  -0.0784   0.8872   0.0272
  -3.250   0.0513   0.00801   0.00287  -0.0781   0.8725   0.0296
  -3.000   0.0787   0.00806   0.00284  -0.0777   0.8548   0.0313
  -2.750   0.1055   0.00783   0.00254  -0.0773   0.8313   0.0346
  -2.500   0.1324   0.00789   0.00249  -0.0768   0.8001   0.0369
  -2.250   0.1594   0.00796   0.00241  -0.0764   0.7689   0.0388
  -2.000   0.1865   0.00784   0.00215  -0.0762   0.7417   0.0409
  -1.750   0.2138   0.00773   0.00195  -0.0759   0.7158   0.0437
  -1.500   0.2412   0.00775   0.00186  -0.0757   0.6891   0.0462
  -1.250   0.2687   0.00778   0.00177  -0.0755   0.6594   0.0484
  -1.000   0.2962   0.00784   0.00170  -0.0753   0.6264   0.0498
  -0.750   0.3234   0.00777   0.00147  -0.0752   0.5907   0.0522
  -0.500   0.3508   0.00778   0.00134  -0.0750   0.5597   0.0562
  -0.250   0.3785   0.00782   0.00128  -0.0749   0.5363   0.0594
   0.000   0.4063   0.00786   0.00124  -0.0748   0.5179   0.0621
   0.250   0.4342   0.00787   0.00118  -0.0748   0.5025   0.0675
   0.500   0.4622   0.00785   0.00116  -0.0747   0.4905   0.0800
   0.750   0.4902   0.00774   0.00120  -0.0748   0.4799   0.1489
   1.000   0.5158   0.00643   0.00133  -0.0751   0.4709   0.7122
   1.250   0.5418   0.00585   0.00137  -0.0743   0.4620   1.0000
   1.500   0.5698   0.00594   0.00140  -0.0743   0.4529   1.0000
   1.750   0.5978   0.00604   0.00144  -0.0742   0.4445   1.0000
   2.000   0.6257   0.00615   0.00148  -0.0742   0.4356   1.0000
   2.250   0.6538   0.00624   0.00153  -0.0741   0.4267   1.0000
   2.500   0.6815   0.00636   0.00159  -0.0741   0.4154   1.0000
   2.750   0.7092   0.00650   0.00166  -0.0740   0.4029   1.0000
   3.000   0.7368   0.00664   0.00173  -0.0739   0.3893   1.0000
   3.250   0.7645   0.00677   0.00181  -0.0739   0.3761   1.0000
   3.500   0.7920   0.00693   0.00191  -0.0738   0.3601   1.0000
   3.750   0.8191   0.00713   0.00202  -0.0737   0.3360   1.0000
   4.000   0.8451   0.00749   0.00218  -0.0734   0.2945   1.0000
   4.250   0.8707   0.00793   0.00240  -0.0732   0.2542   1.0000
   4.500   0.8966   0.00830   0.00263  -0.0729   0.2278   1.0000
   4.750   0.9231   0.00857   0.00283  -0.0727   0.2126   1.0000
   5.000   0.9498   0.00882   0.00302  -0.0726   0.2028   1.0000
   5.250   0.9768   0.00900   0.00320  -0.0725   0.1962   1.0000
   5.500   1.0034   0.00924   0.00341  -0.0723   0.1887   1.0000
   5.750   1.0304   0.00942   0.00359  -0.0722   0.1833   1.0000
   6.000   1.0570   0.00964   0.00379  -0.0720   0.1766   1.0000
   6.250   1.0836   0.00985   0.00401  -0.0719   0.1709   1.0000
   6.500   1.1102   0.01005   0.00421  -0.0717   0.1645   1.0000
   6.750   1.1365   0.01029   0.00444  -0.0716   0.1566   1.0000
   7.000   1.1624   0.01057   0.00468  -0.0713   0.1435   1.0000
   7.250   1.1835   0.01148   0.00523  -0.0706   0.0864   1.0000
   7.500   1.2071   0.01206   0.00574  -0.0700   0.0726   1.0000
   7.750   1.2322   0.01239   0.00609  -0.0697   0.0670   1.0000
   8.000   1.2565   0.01284   0.00653  -0.0692   0.0603   1.0000
   8.250   1.2814   0.01318   0.00689  -0.0689   0.0560   1.0000
   8.500   1.3057   0.01357   0.00727  -0.0685   0.0514   1.0000
   8.750   1.3296   0.01400   0.00771  -0.0680   0.0466   1.0000
   9.000   1.3540   0.01434   0.00808  -0.0676   0.0433   1.0000
   9.250   1.3770   0.01484   0.00855  -0.0670   0.0385   1.0000
   9.500   1.4010   0.01520   0.00895  -0.0665   0.0357   1.0000
   9.750   1.4235   0.01571   0.00943  -0.0659   0.0312   1.0000
  10.000   1.4461   0.01618   0.00993  -0.0653   0.0267   1.0000
  10.250   1.4669   0.01682   0.01054  -0.0644   0.0211   1.0000
  10.500   1.4868   0.01754   0.01124  -0.0634   0.0168   1.0000
  10.750   1.5060   0.01828   0.01200  -0.0624   0.0144   1.0000
  11.000   1.5247   0.01904   0.01281  -0.0612   0.0129   1.0000
  11.250   1.5434   0.01973   0.01358  -0.0601   0.0119   1.0000
  11.500   1.5599   0.02058   0.01448  -0.0586   0.0110   1.0000
  11.750   1.5720   0.02175   0.01575  -0.0566   0.0101   1.0000
  12.000   1.5883   0.02246   0.01654  -0.0552   0.0097   1.0000
  12.250   1.6019   0.02326   0.01742  -0.0534   0.0092   1.0000
  12.500   1.6119   0.02413   0.01836  -0.0511   0.0088   1.0000
  12.750   1.6198   0.02516   0.01946  -0.0486   0.0084   1.0000
  13.000   1.6239   0.02650   0.02090  -0.0460   0.0080   1.0000
  13.250   1.6219   0.02839   0.02291  -0.0431   0.0076   1.0000
  13.500   1.6180   0.03061   0.02527  -0.0406   0.0074   1.0000
  13.750   1.6237   0.03220   0.02696  -0.0392   0.0073   1.0000
  14.000   1.6270   0.03412   0.02900  -0.0380   0.0071   1.0000
  14.250   1.6285   0.03638   0.03137  -0.0371   0.0070   1.0000
  14.500   1.6281   0.03904   0.03414  -0.0366   0.0068   1.0000
  14.750   1.6258   0.04212   0.03735  -0.0365   0.0067   1.0000
  15.000   1.6221   0.04555   0.04090  -0.0368   0.0065   1.0000
  15.250   1.6167   0.04943   0.04491  -0.0375   0.0064   1.0000
  15.500   1.6092   0.05376   0.04936  -0.0386   0.0063   1.0000
  15.750   1.6000   0.05851   0.05423  -0.0400   0.0062   1.0000
  16.000   1.5887   0.06369   0.05955  -0.0417   0.0061   1.0000
  16.250   1.5749   0.06929   0.06528  -0.0435   0.0061   1.0000
  16.500   1.5594   0.07527   0.07138  -0.0456   0.0060   1.0000
  16.750   1.5425   0.08154   0.07779  -0.0479   0.0060   1.0000
  17.000   1.5249   0.08803   0.08440  -0.0503   0.0060   1.0000
  17.250   1.5067   0.09481   0.09129  -0.0529   0.0059   1.0000
  17.500   1.4881   0.10176   0.09836  -0.0557   0.0059   1.0000
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