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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 100,000
Max Cl/Cd: 64.23 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ma409sm-il-100000.txt
Download as CSV file: xf-ma409sm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4176   0.09826   0.09331  -0.0247   1.0000   0.0888
  -7.750  -0.4335   0.09740   0.09260  -0.0263   1.0000   0.0904
  -7.500  -0.4428   0.09575   0.09106  -0.0344   1.0000   0.0912
  -7.250  -0.4298   0.09011   0.08542  -0.0260   1.0000   0.0933
  -7.000  -0.4227   0.08710   0.08243  -0.0241   1.0000   0.0962
  -6.750  -0.4210   0.08436   0.07975  -0.0247   1.0000   0.0997
  -6.500  -0.4206   0.08137   0.07676  -0.0421   1.0000   0.1048
  -6.250  -0.4174   0.07730   0.07279  -0.0334   1.0000   0.1063
  -6.000  -0.4109   0.07453   0.07005  -0.0300   1.0000   0.1091
  -5.750  -0.3983   0.07097   0.06644  -0.0373   1.0000   0.1173
  -5.500  -0.3893   0.06661   0.06209  -0.0390   1.0000   0.1202
  -5.250  -0.3664   0.06305   0.05829  -0.0471   1.0000   0.1320
  -5.000  -0.3589   0.05910   0.05445  -0.0444   1.0000   0.1338
  -4.750  -0.3477   0.05634   0.05172  -0.0424   1.0000   0.1373
  -4.500  -0.2847   0.03937   0.03366  -0.0621   1.0000   0.0751
  -4.250  -0.2506   0.03294   0.02658  -0.0665   1.0000   0.0697
  -4.000  -0.2159   0.02837   0.02124  -0.0693   1.0000   0.0696
  -3.750  -0.1794   0.02445   0.01647  -0.0713   1.0000   0.0689
  -3.500  -0.1471   0.02219   0.01372  -0.0722   1.0000   0.0729
  -3.250  -0.1165   0.02070   0.01194  -0.0728   1.0000   0.0840
  -3.000  -0.0848   0.01921   0.01025  -0.0734   1.0000   0.0973
  -2.750  -0.0552   0.01828   0.00926  -0.0738   1.0000   0.1222
  -2.500  -0.0257   0.01747   0.00843  -0.0742   1.0000   0.1585
  -2.250   0.0032   0.01677   0.00791  -0.0747   1.0000   0.2052
  -2.000   0.0308   0.01638   0.00762  -0.0750   1.0000   0.2575
  -1.750   0.0576   0.01602   0.00748  -0.0751   1.0000   0.3093
  -1.500   0.0849   0.01572   0.00736  -0.0754   1.0000   0.3697
  -1.250   0.1126   0.01531   0.00724  -0.0756   1.0000   0.4453
  -1.000   0.1427   0.01460   0.00713  -0.0762   1.0000   0.5859
  -0.750   0.1501   0.01372   0.00704  -0.0716   1.0000   1.0000
  -0.500   0.1757   0.01403   0.00708  -0.0717   1.0000   1.0000
  -0.250   0.2004   0.01437   0.00723  -0.0718   1.0000   1.0000
   0.000   0.2246   0.01475   0.00745  -0.0717   1.0000   1.0000
   0.250   0.2482   0.01518   0.00776  -0.0717   1.0000   1.0000
   0.500   0.2714   0.01565   0.00814  -0.0717   1.0000   1.0000
   0.750   0.3006   0.01617   0.00859  -0.0730   0.9973   1.0000
   1.000   0.3494   0.01665   0.00901  -0.0778   0.9868   1.0000
   1.250   0.3968   0.01705   0.00938  -0.0822   0.9754   1.0000
   1.500   0.4431   0.01736   0.00969  -0.0863   0.9634   1.0000
   1.750   0.4885   0.01755   0.00992  -0.0900   0.9506   1.0000
   2.000   0.5328   0.01762   0.01005  -0.0932   0.9370   1.0000
   2.250   0.5764   0.01757   0.01009  -0.0960   0.9229   1.0000
   2.500   0.6196   0.01738   0.01005  -0.0986   0.9084   1.0000
   2.750   0.6633   0.01704   0.00984  -0.1008   0.8938   1.0000
   3.000   0.7053   0.01656   0.00952  -0.1025   0.8787   1.0000
   3.250   0.7455   0.01598   0.00915  -0.1035   0.8628   1.0000
   3.500   0.7786   0.01553   0.00887  -0.1031   0.8416   1.0000
   3.750   0.8151   0.01496   0.00845  -0.1031   0.8205   1.0000
   4.000   0.8458   0.01461   0.00823  -0.1021   0.7924   1.0000
   4.250   0.8734   0.01442   0.00814  -0.1007   0.7571   1.0000
   4.500   0.8981   0.01416   0.00786  -0.0980   0.7001   1.0000
   4.750   0.9179   0.01429   0.00769  -0.0947   0.6201   1.0000
   5.000   0.9366   0.01482   0.00790  -0.0919   0.5403   1.0000
   5.250   0.9513   0.01572   0.00830  -0.0888   0.4342   1.0000
   5.500   0.9490   0.01894   0.00953  -0.0838   0.1413   1.0000
   5.750   0.9608   0.02144   0.01147  -0.0809   0.0848   1.0000
   6.000   0.9772   0.02320   0.01326  -0.0786   0.0723   1.0000
   6.250   0.9954   0.02502   0.01503  -0.0769   0.0630   1.0000
   6.500   1.0177   0.02682   0.01682  -0.0756   0.0573   1.0000
   6.750   1.0448   0.03016   0.02004  -0.0752   0.0540   1.0000
   7.000   1.0722   0.03250   0.02266  -0.0742   0.0529   1.0000
   7.250   1.0980   0.03539   0.02592  -0.0731   0.0524   1.0000
   7.500   1.1190   0.03787   0.02889  -0.0713   0.0503   1.0000
   7.750   1.1375   0.04087   0.03237  -0.0694   0.0488   1.0000
   8.000   1.1532   0.04496   0.03704  -0.0672   0.0502   1.0000
   8.250   1.1656   0.04972   0.04223  -0.0650   0.0522   1.0000
   8.500   1.1711   0.05495   0.04841  -0.0609   0.0604   1.0000
  11.000   0.8373   0.12592   0.12184  -0.0582   0.1578   1.0000
  11.250   0.7868   0.13142   0.12723  -0.0652   0.1509   1.0000
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