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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 500,000
Max Cl/Cd: 100.86 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ma409sm-il-500000-n5.txt
Download as CSV file: xf-ma409sm-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4547   0.08313   0.08090  -0.0265   1.0000   0.0074
  -8.000  -0.4672   0.08051   0.07834  -0.0248   1.0000   0.0073
  -7.750  -0.4776   0.07730   0.07518  -0.0244   1.0000   0.0073
  -7.250  -0.4298   0.02671   0.02344  -0.0856   0.9870   0.0074
  -7.000  -0.3987   0.02262   0.01878  -0.0895   0.9852   0.0076
  -6.750  -0.3676   0.01885   0.01438  -0.0926   0.9838   0.0078
  -6.500  -0.3360   0.01662   0.01175  -0.0945   0.9828   0.0082
  -6.250  -0.3087   0.01558   0.01053  -0.0950   0.9800   0.0086
  -6.000  -0.2793   0.01492   0.00977  -0.0957   0.9776   0.0092
  -5.750  -0.2486   0.01405   0.00873  -0.0966   0.9756   0.0096
  -5.500  -0.2169   0.01304   0.00749  -0.0977   0.9740   0.0099
  -5.250  -0.1845   0.01218   0.00648  -0.0989   0.9725   0.0104
  -5.000  -0.1514   0.01147   0.00563  -0.1002   0.9713   0.0110
  -4.750  -0.1176   0.01091   0.00495  -0.1015   0.9702   0.0117
  -4.500  -0.0888   0.01032   0.00426  -0.1018   0.9668   0.0131
  -4.250  -0.0586   0.00990   0.00377  -0.1023   0.9636   0.0153
  -4.000  -0.0269   0.00958   0.00340  -0.1032   0.9611   0.0181
  -3.750   0.0054   0.00921   0.00304  -0.1042   0.9588   0.0248
  -3.500   0.0386   0.00890   0.00273  -0.1053   0.9567   0.0336
  -3.250   0.0658   0.00865   0.00249  -0.1051   0.9504   0.0445
  -3.000   0.0972   0.00835   0.00223  -0.1058   0.9455   0.0637
  -2.750   0.1273   0.00807   0.00203  -0.1063   0.9395   0.0873
  -2.500   0.1569   0.00787   0.00186  -0.1066   0.9330   0.1069
  -2.250   0.1870   0.00767   0.00171  -0.1071   0.9271   0.1304
  -2.000   0.2159   0.00749   0.00158  -0.1072   0.9198   0.1522
  -1.750   0.2453   0.00732   0.00147  -0.1075   0.9126   0.1779
  -1.500   0.2743   0.00716   0.00137  -0.1077   0.9042   0.2061
  -1.250   0.3028   0.00702   0.00129  -0.1077   0.8945   0.2349
  -1.000   0.3313   0.00690   0.00122  -0.1078   0.8840   0.2663
  -0.750   0.3596   0.00678   0.00116  -0.1078   0.8721   0.3008
  -0.500   0.3876   0.00669   0.00113  -0.1077   0.8586   0.3360
  -0.250   0.4152   0.00661   0.00110  -0.1076   0.8432   0.3730
   0.000   0.4424   0.00655   0.00109  -0.1073   0.8258   0.4120
   0.500   0.4958   0.00641   0.00111  -0.1067   0.7856   0.5172
   0.750   0.5212   0.00619   0.00117  -0.1061   0.7626   0.6424
   1.250   0.5693   0.00573   0.00125  -0.1038   0.7095   1.0000
   1.500   0.5949   0.00593   0.00131  -0.1032   0.6788   1.0000
   1.750   0.6203   0.00615   0.00138  -0.1026   0.6460   1.0000
   2.000   0.6454   0.00640   0.00150  -0.1020   0.6119   1.0000
   2.250   0.6706   0.00666   0.00161  -0.1014   0.5771   1.0000
   2.500   0.6957   0.00694   0.00175  -0.1008   0.5428   1.0000
   2.750   0.7211   0.00721   0.00190  -0.1003   0.5101   1.0000
   3.000   0.7463   0.00750   0.00208  -0.0998   0.4776   1.0000
   3.250   0.7697   0.00799   0.00230  -0.0990   0.4186   1.0000
   3.500   0.7920   0.00863   0.00257  -0.0981   0.3388   1.0000
   3.750   0.8151   0.00922   0.00285  -0.0973   0.2716   1.0000
   4.000   0.8376   0.00994   0.00320  -0.0965   0.1972   1.0000
   4.250   0.8599   0.01069   0.00363  -0.0958   0.1262   1.0000
   4.500   0.8816   0.01156   0.00414  -0.0949   0.0570   1.0000
   4.750   0.9056   0.01210   0.00456  -0.0942   0.0328   1.0000
   5.000   0.9304   0.01253   0.00495  -0.0937   0.0228   1.0000
   5.250   0.9554   0.01292   0.00537  -0.0932   0.0182   1.0000
   5.500   0.9799   0.01338   0.00584  -0.0926   0.0150   1.0000
   5.750   1.0035   0.01400   0.00656  -0.0917   0.0130   1.0000
   6.000   1.0277   0.01448   0.00711  -0.0910   0.0122   1.0000
   6.250   1.0516   0.01496   0.00765  -0.0904   0.0111   1.0000
   6.500   1.0751   0.01551   0.00826  -0.0896   0.0103   1.0000
   6.750   1.0980   0.01612   0.00893  -0.0888   0.0097   1.0000
   7.000   1.1198   0.01686   0.00974  -0.0878   0.0090   1.0000
   7.250   1.1387   0.01802   0.01104  -0.0863   0.0084   1.0000
   7.500   1.1593   0.01892   0.01204  -0.0851   0.0079   1.0000
   7.750   1.1816   0.01952   0.01273  -0.0842   0.0074   1.0000
   8.000   1.2030   0.02025   0.01355  -0.0832   0.0068   1.0000
   8.250   1.2230   0.02118   0.01459  -0.0820   0.0064   1.0000
   8.500   1.2428   0.02209   0.01561  -0.0807   0.0060   1.0000
   8.750   1.2623   0.02301   0.01662  -0.0795   0.0057   1.0000
   9.000   1.2807   0.02403   0.01774  -0.0782   0.0054   1.0000
   9.250   1.2956   0.02561   0.01950  -0.0764   0.0050   1.0000
   9.500   1.3070   0.02792   0.02207  -0.0740   0.0048   1.0000
   9.750   1.3219   0.02943   0.02379  -0.0722   0.0046   1.0000
  10.000   1.3341   0.03130   0.02592  -0.0700   0.0045   1.0000
  10.250   1.3428   0.03355   0.02846  -0.0675   0.0043   1.0000
  10.500   1.3477   0.03610   0.03131  -0.0646   0.0042   1.0000
  10.750   1.3478   0.03868   0.03419  -0.0611   0.0040   1.0000
  11.000   1.3428   0.04133   0.03711  -0.0572   0.0039   1.0000
  11.250   1.3343   0.04419   0.04025  -0.0534   0.0038   1.0000
  11.500   1.3226   0.04742   0.04373  -0.0500   0.0037   1.0000
  11.750   1.3087   0.05103   0.04759  -0.0474   0.0036   1.0000
  12.000   1.2899   0.05558   0.05239  -0.0458   0.0036   1.0000
  12.250   1.2709   0.06063   0.05768  -0.0455   0.0035   1.0000
  12.500   1.2469   0.06717   0.06446  -0.0471   0.0036   1.0000
  12.750   1.2221   0.07495   0.07246  -0.0507   0.0036   1.0000
  13.000   1.1932   0.08494   0.08266  -0.0569   0.0037   1.0000
  13.250   1.1617   0.09747   0.09538  -0.0655   0.0038   1.0000
  13.750   0.9903   0.10297   0.10088  -0.0514   0.0043   1.0000
  14.000   0.9624   0.11214   0.11014  -0.0558   0.0044   1.0000
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