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MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MA409 (original) (modified line 7) (ma409-il)
Reynolds number: 100,000
Max Cl/Cd: 61.88 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ma409-il-100000.txt
Download as CSV file: xf-ma409-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MA409 (original)                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4259   0.09809   0.09342  -0.0258   1.0000   0.0858
  -8.750  -0.4407   0.09691   0.09240  -0.0283   1.0000   0.0867
  -8.500  -0.4463   0.09446   0.09003  -0.0352   1.0000   0.0872
  -8.250  -0.4390   0.08914   0.08476  -0.0294   1.0000   0.0885
  -8.000  -0.4312   0.08577   0.08140  -0.0260   1.0000   0.0905
  -7.750  -0.4280   0.08287   0.07854  -0.0256   1.0000   0.0928
  -7.500  -0.4261   0.07986   0.07557  -0.0268   1.0000   0.0958
  -7.250  -0.4188   0.07519   0.07081  -0.0447   1.0000   0.1010
  -7.000  -0.4167   0.07138   0.06712  -0.0383   1.0000   0.1022
  -6.750  -0.4113   0.06861   0.06439  -0.0350   1.0000   0.1042
  -6.500  -0.4030   0.06556   0.06130  -0.0352   1.0000   0.1078
  -6.250  -0.3843   0.05986   0.05542  -0.0447   1.0000   0.1159
  -6.000  -0.3392   0.04044   0.03499  -0.0608   1.0000   0.0587
  -5.750  -0.3095   0.03470   0.02840  -0.0646   1.0000   0.0599
  -5.500  -0.2919   0.03314   0.02701  -0.0643   1.0000   0.0662
  -5.250  -0.2563   0.02796   0.02093  -0.0674   1.0000   0.0686
  -5.000  -0.2213   0.02431   0.01649  -0.0693   1.0000   0.0775
  -4.750  -0.1919   0.02284   0.01464  -0.0701   1.0000   0.1030
  -4.500  -0.1667   0.02239   0.01404  -0.0700   1.0000   0.1264
  -4.250  -0.1440   0.02218   0.01391  -0.0699   1.0000   0.1481
  -4.000  -0.1147   0.02116   0.01243  -0.0702   1.0000   0.1541
  -3.750  -0.0861   0.02019   0.01122  -0.0705   1.0000   0.1587
  -3.500  -0.0591   0.01956   0.01049  -0.0706   1.0000   0.1654
  -3.250  -0.0319   0.01898   0.00982  -0.0707   1.0000   0.1741
  -3.000  -0.0045   0.01851   0.00924  -0.0708   1.0000   0.1828
  -2.750   0.0232   0.01799   0.00875  -0.0710   1.0000   0.1934
  -2.500   0.0509   0.01758   0.00840  -0.0712   1.0000   0.2104
  -2.250   0.0793   0.01718   0.00822  -0.0716   1.0000   0.2445
  -2.000   0.1116   0.01643   0.00814  -0.0728   1.0000   0.3774
  -1.750   0.1445   0.01550   0.00810  -0.0738   1.0000   0.6111
  -1.500   0.1520   0.01482   0.00803  -0.0693   1.0000   1.0000
  -1.250   0.1776   0.01511   0.00808  -0.0694   1.0000   1.0000
  -1.000   0.2029   0.01542   0.00822  -0.0694   1.0000   1.0000
  -0.750   0.2356   0.01577   0.00843  -0.0709   0.9969   1.0000
  -0.500   0.2793   0.01615   0.00867  -0.0745   0.9891   1.0000
  -0.250   0.3264   0.01654   0.00896  -0.0787   0.9816   1.0000
   0.000   0.3655   0.01682   0.00919  -0.0813   0.9728   1.0000
   0.250   0.4055   0.01708   0.00945  -0.0840   0.9639   1.0000
   0.500   0.4520   0.01729   0.00967  -0.0879   0.9559   1.0000
   0.750   0.4882   0.01743   0.00985  -0.0897   0.9447   1.0000
   1.000   0.5267   0.01751   0.01000  -0.0917   0.9333   1.0000
   1.250   0.5674   0.01747   0.01009  -0.0940   0.9207   1.0000
   1.500   0.6110   0.01719   0.00994  -0.0965   0.9059   1.0000
   1.750   0.6571   0.01665   0.00955  -0.0989   0.8900   1.0000
   2.000   0.6994   0.01599   0.00910  -0.1003   0.8739   1.0000
   2.250   0.7307   0.01554   0.00881  -0.0998   0.8524   1.0000
   2.500   0.7667   0.01487   0.00831  -0.0997   0.8299   1.0000
   2.750   0.8013   0.01425   0.00782  -0.0991   0.8001   1.0000
   3.000   0.8367   0.01376   0.00722  -0.0978   0.7465   1.0000
   3.250   0.8530   0.01396   0.00747  -0.0946   0.6720   1.0000
   3.500   0.8731   0.01411   0.00693  -0.0913   0.5759   1.0000
   3.750   0.8917   0.01505   0.00762  -0.0891   0.4974   1.0000
   4.000   0.9066   0.01588   0.00799  -0.0863   0.3826   1.0000
   4.250   0.9143   0.01819   0.00888  -0.0830   0.1615   1.0000
   4.500   0.9272   0.02072   0.01067  -0.0805   0.0680   1.0000
   4.750   0.9463   0.02208   0.01204  -0.0788   0.0551   1.0000
   5.000   0.9641   0.02356   0.01356  -0.0770   0.0495   1.0000
   5.250   0.9823   0.02528   0.01534  -0.0750   0.0472   1.0000
   5.500   1.0044   0.02711   0.01725  -0.0735   0.0457   1.0000
   5.750   1.0300   0.02934   0.01958  -0.0725   0.0449   1.0000
   6.000   1.0571   0.03190   0.02234  -0.0717   0.0443   1.0000
   6.250   1.0815   0.03429   0.02505  -0.0707   0.0422   1.0000
   6.500   1.1040   0.03701   0.02808  -0.0695   0.0410   1.0000
   6.750   1.1234   0.04088   0.03258  -0.0674   0.0429   1.0000
   7.000   1.1385   0.04520   0.03743  -0.0651   0.0452   1.0000
   7.250   1.1507   0.05015   0.04273  -0.0632   0.0474   1.0000
   7.500   1.1539   0.05530   0.04887  -0.0590   0.0546   1.0000
   8.250   1.0389   0.06532   0.06072  -0.0394   0.0781   1.0000
   8.500   1.0085   0.06999   0.06558  -0.0362   0.0794   1.0000
   8.750   0.9801   0.07450   0.07023  -0.0345   0.0790   1.0000
   9.000   0.9530   0.07942   0.07525  -0.0343   0.0779   1.0000
   9.250   0.9273   0.08504   0.08094  -0.0354   0.0769   1.0000
   9.500   0.9019   0.09148   0.08744  -0.0378   0.0762   1.0000
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