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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 200,000
Max Cl/Cd: 88.56 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ma409sm-il-200000.txt
Download as CSV file: xf-ma409sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MA409 (smoothed)                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4271   0.08722   0.08382  -0.0247   1.0000   0.0433
  -7.250  -0.4296   0.08480   0.08146  -0.0241   1.0000   0.0444
  -7.000  -0.4305   0.08206   0.07876  -0.0245   1.0000   0.0458
  -6.750  -0.4307   0.07903   0.07578  -0.0258   1.0000   0.0474
  -6.500  -0.4280   0.07527   0.07206  -0.0301   1.0000   0.0498
  -6.250  -0.4092   0.06897   0.06565  -0.0441   1.0000   0.0517
  -6.000  -0.3950   0.05677   0.05389  -0.0285   1.0000   0.0541
  -5.750  -0.4065   0.06274   0.05952  -0.0387   1.0000   0.0549
  -5.500  -0.3955   0.06025   0.05701  -0.0390   1.0000   0.0581
  -5.250  -0.3594   0.05003   0.04634  -0.0546   1.0000   0.0656
  -5.000  -0.3477   0.04766   0.04404  -0.0531   1.0000   0.0669
  -4.750  -0.3309   0.04517   0.04152  -0.0532   1.0000   0.0690
  -4.500  -0.2666   0.02664   0.02130  -0.0675   1.0000   0.0368
  -4.250  -0.2300   0.02206   0.01595  -0.0702   1.0000   0.0348
  -4.000  -0.1949   0.01937   0.01266  -0.0717   1.0000   0.0353
  -3.750  -0.1628   0.01771   0.01057  -0.0724   1.0000   0.0373
  -3.500  -0.1315   0.01627   0.00891  -0.0733   1.0000   0.0425
  -3.250  -0.1023   0.01545   0.00799  -0.0737   1.0000   0.0488
  -3.000  -0.0711   0.01445   0.00695  -0.0745   1.0000   0.0595
  -2.750  -0.0417   0.01388   0.00636  -0.0750   1.0000   0.0795
  -2.500  -0.0127   0.01343   0.00601  -0.0756   1.0000   0.1130
  -2.250   0.0156   0.01313   0.00584  -0.0761   1.0000   0.1553
  -2.000   0.0426   0.01298   0.00581  -0.0764   1.0000   0.1954
  -1.750   0.0815   0.01283   0.00578  -0.0790   0.9968   0.2445
  -1.500   0.1240   0.01264   0.00579  -0.0824   0.9932   0.3047
  -1.250   0.1642   0.01242   0.00580  -0.0853   0.9879   0.3770
  -1.000   0.2067   0.01212   0.00582  -0.0886   0.9842   0.4714
  -0.750   0.2437   0.01129   0.00587  -0.0906   0.9809   0.7000
  -0.500   0.2740   0.01082   0.00574  -0.0904   0.9726   1.0000
  -0.250   0.3131   0.01088   0.00567  -0.0928   0.9662   1.0000
   0.000   0.3526   0.01088   0.00559  -0.0952   0.9594   1.0000
   0.250   0.3904   0.01087   0.00551  -0.0972   0.9522   1.0000
   0.500   0.4303   0.01078   0.00539  -0.0995   0.9454   1.0000
   0.750   0.4662   0.01069   0.00527  -0.1010   0.9369   1.0000
   1.000   0.5082   0.01049   0.00508  -0.1035   0.9310   1.0000
   1.250   0.5414   0.01033   0.00492  -0.1042   0.9211   1.0000
   1.500   0.5769   0.01009   0.00471  -0.1053   0.9124   1.0000
   1.750   0.6121   0.00982   0.00447  -0.1061   0.9030   1.0000
   2.000   0.6426   0.00962   0.00432  -0.1060   0.8900   1.0000
   2.250   0.6731   0.00942   0.00415  -0.1059   0.8758   1.0000
   2.500   0.7013   0.00929   0.00406  -0.1053   0.8578   1.0000
   2.750   0.7299   0.00919   0.00398  -0.1048   0.8376   1.0000
   3.000   0.7578   0.00915   0.00398  -0.1042   0.8141   1.0000
   3.250   0.7851   0.00917   0.00399  -0.1035   0.7871   1.0000
   3.500   0.8114   0.00926   0.00405  -0.1026   0.7558   1.0000
   3.750   0.8360   0.00944   0.00411  -0.1012   0.7125   1.0000
   4.000   0.8570   0.00982   0.00417  -0.0992   0.6419   1.0000
   4.250   0.8770   0.01036   0.00441  -0.0972   0.5682   1.0000
   4.500   0.8964   0.01101   0.00473  -0.0953   0.4946   1.0000
   4.750   0.9148   0.01179   0.00513  -0.0934   0.4117   1.0000
   5.000   0.9311   0.01288   0.00566  -0.0914   0.2974   1.0000
   5.250   0.9364   0.01585   0.00710  -0.0883   0.0682   1.0000
   5.500   0.9558   0.01714   0.00835  -0.0866   0.0465   1.0000
   5.750   0.9740   0.01854   0.00980  -0.0848   0.0402   1.0000
   6.000   0.9942   0.01972   0.01111  -0.0832   0.0367   1.0000
   6.250   1.0142   0.02108   0.01251  -0.0816   0.0343   1.0000
   6.500   1.0347   0.02283   0.01428  -0.0802   0.0325   1.0000
   6.750   1.0566   0.02542   0.01695  -0.0791   0.0300   1.0000
   7.000   1.0808   0.02697   0.01871  -0.0780   0.0288   1.0000
   7.250   1.1048   0.02929   0.02129  -0.0769   0.0282   1.0000
   7.500   1.1273   0.03220   0.02455  -0.0754   0.0282   1.0000
   7.750   1.1465   0.03582   0.02862  -0.0736   0.0287   1.0000
   8.000   1.1630   0.03875   0.03197  -0.0715   0.0281   1.0000
   8.250   1.1763   0.04192   0.03557  -0.0691   0.0274   1.0000
   8.500   1.1818   0.04759   0.04166  -0.0664   0.0294   1.0000
  12.500   0.8199   0.13407   0.13112  -0.0547   0.0539   1.0000
  12.750   0.8025   0.13951   0.13654  -0.0579   0.0538   1.0000
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