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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 50,000
Max Cl/Cd: 43.56 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ma409sm-il-50000-n5.txt
Download as CSV file: xf-ma409sm-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4311   0.09395   0.08696  -0.0285   1.0000   0.0504
  -7.500  -0.4290   0.09062   0.08369  -0.0290   1.0000   0.0497
  -7.250  -0.4273   0.08716   0.08032  -0.0304   1.0000   0.0494
  -7.000  -0.4248   0.08351   0.07673  -0.0323   1.0000   0.0493
  -6.750  -0.4208   0.07959   0.07287  -0.0348   1.0000   0.0495
  -6.500  -0.4149   0.07539   0.06869  -0.0378   1.0000   0.0496
  -6.250  -0.4067   0.07084   0.06415  -0.0413   1.0000   0.0497
  -6.000  -0.3957   0.06598   0.05925  -0.0451   1.0000   0.0498
  -5.750  -0.3817   0.06081   0.05399  -0.0490   1.0000   0.0496
  -5.500  -0.3646   0.05537   0.04838  -0.0531   1.0000   0.0491
  -5.250  -0.3434   0.04954   0.04227  -0.0577   1.0000   0.0487
  -5.000  -0.3179   0.04370   0.03596  -0.0623   1.0000   0.0488
  -4.750  -0.2891   0.03826   0.02986  -0.0662   1.0000   0.0494
  -4.500  -0.2578   0.03358   0.02430  -0.0691   1.0000   0.0512
  -4.250  -0.2333   0.03161   0.02217  -0.0698   1.0000   0.0566
  -4.000  -0.2037   0.02897   0.01889  -0.0709   1.0000   0.0624
  -3.750  -0.1745   0.02661   0.01602  -0.0714   1.0000   0.0670
  -3.500  -0.1469   0.02520   0.01427  -0.0716   1.0000   0.0785
  -3.250  -0.1197   0.02389   0.01272  -0.0716   1.0000   0.0908
  -3.000  -0.0928   0.02288   0.01169  -0.0717   1.0000   0.1094
  -2.750  -0.0650   0.02196   0.01064  -0.0718   1.0000   0.1352
  -2.250  -0.0098   0.02078   0.00940  -0.0723   1.0000   0.2175
  -2.000   0.0174   0.02035   0.00904  -0.0725   1.0000   0.2647
  -1.750   0.0443   0.01997   0.00875  -0.0726   1.0000   0.3166
  -1.500   0.0712   0.01961   0.00853  -0.0727   1.0000   0.3756
  -1.250   0.0978   0.01921   0.00830  -0.0728   1.0000   0.4479
  -1.000   0.1233   0.01861   0.00815  -0.0724   1.0000   0.5569
  -0.750   0.1281   0.01753   0.00800  -0.0673   1.0000   1.0000
  -0.500   0.1538   0.01781   0.00792  -0.0674   1.0000   1.0000
  -0.250   0.1786   0.01812   0.00797  -0.0674   1.0000   1.0000
   0.000   0.2029   0.01847   0.00807  -0.0674   1.0000   1.0000
   0.250   0.2300   0.01886   0.00828  -0.0680   0.9981   1.0000
   0.500   0.2718   0.01929   0.00855  -0.0714   0.9880   1.0000
   0.750   0.3129   0.01970   0.00884  -0.0745   0.9776   1.0000
   1.000   0.3537   0.02008   0.00913  -0.0776   0.9668   1.0000
   1.250   0.3943   0.02040   0.00941  -0.0805   0.9555   1.0000
   1.500   0.4336   0.02067   0.00968  -0.0830   0.9432   1.0000
   1.750   0.4711   0.02089   0.00995  -0.0850   0.9300   1.0000
   2.000   0.5084   0.02106   0.01017  -0.0870   0.9162   1.0000
   2.250   0.5442   0.02118   0.01038  -0.0884   0.9013   1.0000
   2.500   0.5788   0.02126   0.01062  -0.0895   0.8852   1.0000
   2.750   0.6143   0.02128   0.01078  -0.0906   0.8688   1.0000
   3.000   0.6496   0.02121   0.01087  -0.0915   0.8518   1.0000
   3.250   0.6855   0.02106   0.01090  -0.0922   0.8345   1.0000
   3.500   0.7154   0.02101   0.01110  -0.0918   0.8124   1.0000
   3.750   0.7487   0.02084   0.01114  -0.0918   0.7908   1.0000
   4.000   0.7807   0.02070   0.01120  -0.0914   0.7659   1.0000
   4.250   0.8115   0.02059   0.01130  -0.0907   0.7377   1.0000
   4.500   0.8400   0.02061   0.01151  -0.0897   0.7048   1.0000
   4.750   0.8697   0.02062   0.01176  -0.0887   0.6691   1.0000
   5.000   0.8967   0.02078   0.01206  -0.0873   0.6274   1.0000
   5.250   0.9169   0.02105   0.01214  -0.0842   0.5529   1.0000
   5.500   0.9282   0.02193   0.01228  -0.0800   0.4322   1.0000
   5.750   0.9397   0.02328   0.01303  -0.0770   0.3114   1.0000
   6.000   0.9484   0.02572   0.01441  -0.0745   0.1540   1.0000
   6.250   0.9618   0.02839   0.01648  -0.0728   0.0895   1.0000
   6.500   0.9788   0.03038   0.01848  -0.0711   0.0725   1.0000
   6.750   0.9960   0.03221   0.02039  -0.0695   0.0608   1.0000
   7.000   1.0130   0.03420   0.02243  -0.0678   0.0547   1.0000
   7.250   1.0349   0.03626   0.02474  -0.0663   0.0510   1.0000
   7.500   1.0582   0.03840   0.02713  -0.0651   0.0466   1.0000
   7.750   1.0785   0.04104   0.02976  -0.0643   0.0420   1.0000
   8.000   1.1016   0.04363   0.03281  -0.0631   0.0396   1.0000
   8.250   1.1224   0.04681   0.03656  -0.0618   0.0383   1.0000
   8.500   1.1386   0.05029   0.04054  -0.0601   0.0374   1.0000
   8.750   1.1499   0.05402   0.04478  -0.0581   0.0367   1.0000
   9.000   1.1562   0.05793   0.04918  -0.0559   0.0364   1.0000
   9.250   1.1574   0.06197   0.05370  -0.0535   0.0361   1.0000
   9.500   1.1539   0.06601   0.05815  -0.0511   0.0358   1.0000
   9.750   1.1458   0.07002   0.06252  -0.0488   0.0355   1.0000
  10.000   1.1325   0.07393   0.06672  -0.0464   0.0353   1.0000
  10.250   1.1150   0.07800   0.07104  -0.0445   0.0353   1.0000
  10.500   1.0948   0.08264   0.07590  -0.0438   0.0356   1.0000
  10.750   1.0730   0.08807   0.08153  -0.0448   0.0360   1.0000
  11.000   1.0508   0.09450   0.08811  -0.0477   0.0367   1.0000
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