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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 500,000
Max Cl/Cd: 94.9 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe673-il-500000-n5.txt
Download as CSV file: xf-goe673-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4457   0.08455   0.08240  -0.0426   1.0000   0.0046
  -9.250  -0.4566   0.07840   0.07630  -0.0453   1.0000   0.0045
  -9.000  -0.4827   0.07101   0.06903  -0.0473   1.0000   0.0043
  -8.750  -0.4911   0.05112   0.04897  -0.0700   0.9892   0.0041
  -8.500  -0.4913   0.04217   0.03961  -0.0785   0.9807   0.0040
  -8.250  -0.4881   0.03453   0.03142  -0.0823   0.9725   0.0042
  -8.000  -0.4690   0.03162   0.02822  -0.0841   0.9669   0.0044
  -7.750  -0.4494   0.02970   0.02608  -0.0847   0.9593   0.0046
  -7.500  -0.4274   0.02759   0.02370  -0.0853   0.9538   0.0049
  -7.250  -0.4096   0.02442   0.02008  -0.0848   0.9465   0.0050
  -7.000  -0.3886   0.02141   0.01662  -0.0844   0.9409   0.0050
  -6.750  -0.3662   0.01924   0.01410  -0.0839   0.9348   0.0052
  -6.500  -0.3422   0.01750   0.01207  -0.0834   0.9291   0.0054
  -6.250  -0.3174   0.01609   0.01043  -0.0830   0.9239   0.0057
  -6.000  -0.2924   0.01497   0.00912  -0.0826   0.9179   0.0060
  -5.750  -0.2665   0.01409   0.00808  -0.0823   0.9128   0.0063
  -5.500  -0.2415   0.01306   0.00692  -0.0821   0.9066   0.0068
  -5.250  -0.2150   0.01262   0.00642  -0.0821   0.9007   0.0076
  -5.000  -0.1883   0.01213   0.00586  -0.0820   0.8949   0.0084
  -4.750  -0.1617   0.01154   0.00516  -0.0819   0.8884   0.0091
  -4.500  -0.1346   0.01107   0.00459  -0.0818   0.8824   0.0099
  -4.250  -0.1076   0.01049   0.00388  -0.0818   0.8755   0.0113
  -4.000  -0.0801   0.01010   0.00340  -0.0818   0.8690   0.0142
  -3.750  -0.0524   0.00982   0.00303  -0.0818   0.8615   0.0168
  -3.500  -0.0245   0.00958   0.00270  -0.0819   0.8543   0.0228
  -3.250   0.0026   0.00906   0.00236  -0.0820   0.8462   0.0787
  -3.000   0.0296   0.00854   0.00212  -0.0823   0.8381   0.1665
  -2.500   0.0841   0.00773   0.00182  -0.0827   0.8204   0.3336
  -2.250   0.1117   0.00749   0.00172  -0.0829   0.8115   0.3929
  -2.000   0.1396   0.00738   0.00163  -0.0830   0.8020   0.4272
  -1.750   0.1677   0.00727   0.00156  -0.0832   0.7916   0.4604
  -1.500   0.1957   0.00720   0.00149  -0.0833   0.7811   0.4869
  -1.250   0.2236   0.00712   0.00143  -0.0834   0.7700   0.5140
  -1.000   0.2514   0.00706   0.00138  -0.0835   0.7582   0.5417
  -0.750   0.2791   0.00698   0.00136  -0.0836   0.7455   0.5757
  -0.500   0.3065   0.00690   0.00136  -0.0836   0.7322   0.6231
  -0.250   0.3338   0.00685   0.00138  -0.0835   0.7184   0.6672
   0.000   0.3610   0.00683   0.00140  -0.0834   0.7041   0.7036
   0.250   0.3881   0.00682   0.00142  -0.0833   0.6897   0.7336
   0.500   0.4150   0.00683   0.00145  -0.0832   0.6751   0.7607
   0.750   0.4414   0.00683   0.00150  -0.0829   0.6608   0.7923
   1.000   0.4669   0.00681   0.00155  -0.0824   0.6467   0.8283
   1.250   0.4903   0.00679   0.00163  -0.0813   0.6329   0.8752
   1.500   0.5140   0.00681   0.00170  -0.0802   0.6190   0.9287
   1.750   0.5440   0.00688   0.00174  -0.0807   0.6038   0.9667
   2.250   0.6051   0.00713   0.00188  -0.0822   0.5730   1.0000
   2.500   0.6322   0.00727   0.00198  -0.0822   0.5594   1.0000
   2.750   0.6594   0.00741   0.00209  -0.0823   0.5459   1.0000
   3.000   0.6866   0.00755   0.00223  -0.0823   0.5332   1.0000
   3.250   0.7137   0.00770   0.00237  -0.0823   0.5198   1.0000
   3.500   0.7406   0.00786   0.00252  -0.0823   0.5057   1.0000
   3.750   0.7668   0.00808   0.00270  -0.0821   0.4855   1.0000
   4.000   0.7907   0.00849   0.00291  -0.0816   0.4403   1.0000
   4.250   0.8127   0.00907   0.00320  -0.0808   0.3768   1.0000
   4.500   0.8326   0.00991   0.00361  -0.0798   0.2902   1.0000
   4.750   0.8484   0.01121   0.00427  -0.0782   0.1666   1.0000
   5.000   0.8609   0.01292   0.00527  -0.0761   0.0238   1.0000
   5.250   0.8848   0.01339   0.00575  -0.0755   0.0142   1.0000
   5.500   0.9092   0.01378   0.00619  -0.0751   0.0118   1.0000
   5.750   0.9328   0.01424   0.00670  -0.0745   0.0098   1.0000
   6.000   0.9540   0.01495   0.00751  -0.0734   0.0082   1.0000
   6.250   0.9757   0.01558   0.00825  -0.0725   0.0076   1.0000
   6.500   0.9978   0.01611   0.00884  -0.0717   0.0068   1.0000
   6.750   1.0194   0.01666   0.00943  -0.0708   0.0060   1.0000
   7.000   1.0393   0.01735   0.01017  -0.0697   0.0056   1.0000
   7.250   1.0549   0.01839   0.01129  -0.0678   0.0052   1.0000
   7.500   1.0702   0.01940   0.01241  -0.0659   0.0050   1.0000
   7.750   1.0858   0.02037   0.01348  -0.0640   0.0047   1.0000
   8.000   1.0997   0.02146   0.01468  -0.0619   0.0045   1.0000
   8.250   1.1121   0.02265   0.01597  -0.0595   0.0043   1.0000
   8.500   1.1237   0.02387   0.01731  -0.0570   0.0042   1.0000
   8.750   1.1370   0.02499   0.01853  -0.0550   0.0039   1.0000
   9.000   1.1511   0.02591   0.01957  -0.0532   0.0037   1.0000
   9.250   1.1646   0.02683   0.02056  -0.0515   0.0035   1.0000
   9.500   1.1764   0.02795   0.02175  -0.0496   0.0033   1.0000
   9.750   1.1852   0.02999   0.02394  -0.0473   0.0031   1.0000
  10.000   1.1964   0.03174   0.02591  -0.0453   0.0031   1.0000
  10.250   1.2061   0.03387   0.02828  -0.0432   0.0030   1.0000
  10.500   1.2131   0.03652   0.03123  -0.0407   0.0028   1.0000
  10.750   1.2156   0.03978   0.03482  -0.0380   0.0027   1.0000
  11.000   1.2121   0.04356   0.03894  -0.0349   0.0027   1.0000
  11.250   1.2028   0.04781   0.04353  -0.0317   0.0026   1.0000
  11.500   1.1904   0.05199   0.04801  -0.0290   0.0026   1.0000
  11.750   1.1751   0.05649   0.05277  -0.0268   0.0026   1.0000
  12.000   1.1576   0.06130   0.05783  -0.0254   0.0025   1.0000
  12.250   1.1388   0.06648   0.06324  -0.0248   0.0025   1.0000
  12.500   1.1192   0.07201   0.06897  -0.0252   0.0026   1.0000
  12.750   1.0995   0.07795   0.07509  -0.0266   0.0026   1.0000
  13.000   1.0792   0.08443   0.08174  -0.0290   0.0026   1.0000
  13.250   1.0585   0.09156   0.08904  -0.0322   0.0026   1.0000
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