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dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: dh4009sm (dh4009sm-il)
Reynolds number: 50,000
Max Cl/Cd: 24.19 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dh4009sm-il-50000-n5.txt
Download as CSV file: xf-dh4009sm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: dh4009sm                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6085   0.06193   0.05509  -0.0272   1.0000   0.0672
  -7.750  -0.6803   0.06985   0.06235  -0.0218   1.0000   0.0599
  -7.500  -0.6770   0.06584   0.05811  -0.0209   1.0000   0.0577
  -7.250  -0.6731   0.06193   0.05395  -0.0197   1.0000   0.0552
  -7.000  -0.6668   0.05956   0.05076  -0.0172   1.0000   0.0493
  -6.750  -0.6554   0.05532   0.04643  -0.0162   1.0000   0.0483
  -6.500  -0.6440   0.05167   0.04257  -0.0148   1.0000   0.0469
  -6.250  -0.6312   0.04831   0.03892  -0.0132   1.0000   0.0451
  -6.000  -0.6165   0.04520   0.03544  -0.0115   1.0000   0.0435
  -5.750  -0.5999   0.04229   0.03210  -0.0097   1.0000   0.0420
  -5.500  -0.5810   0.03958   0.02896  -0.0079   1.0000   0.0407
  -5.250  -0.5601   0.03709   0.02603  -0.0063   1.0000   0.0398
  -5.000  -0.5374   0.03483   0.02336  -0.0049   1.0000   0.0392
  -4.750  -0.5133   0.03274   0.02091  -0.0036   1.0000   0.0389
  -4.500  -0.4877   0.03079   0.01863  -0.0027   1.0000   0.0390
  -4.250  -0.4606   0.02900   0.01668  -0.0019   1.0000   0.0395
  -4.000  -0.4338   0.02749   0.01508  -0.0011   1.0000   0.0418
  -3.750  -0.4087   0.02632   0.01377  -0.0001   1.0000   0.0460
  -3.500  -0.3858   0.02530   0.01255   0.0014   1.0000   0.0489
  -3.250  -0.3665   0.02413   0.01126   0.0031   1.0000   0.0508
  -3.000  -0.3488   0.02301   0.00997   0.0048   1.0000   0.0540
  -2.750  -0.3298   0.02210   0.00890   0.0063   1.0000   0.0591
  -2.500  -0.3111   0.02116   0.00789   0.0077   1.0000   0.0727
  -2.250  -0.2973   0.01927   0.00681   0.0094   1.0000   0.1885
  -2.000  -0.2099   0.01990   0.00974   0.0101   1.0000   0.9401
  -1.750  -0.1753   0.01960   0.00909   0.0080   1.0000   0.9482
  -1.500  -0.1436   0.01932   0.00859   0.0064   1.0000   0.9578
  -1.250  -0.1068   0.01905   0.00813   0.0037   1.0000   0.9657
  -1.000  -0.0724   0.01881   0.00776   0.0014   1.0000   0.9746
  -0.750  -0.0381   0.01860   0.00743  -0.0009   1.0000   0.9842
  -0.500  -0.0022   0.01839   0.00716  -0.0037   1.0000   0.9933
  -0.250   0.0250   0.01822   0.00698  -0.0048   1.0000   1.0000
   0.000   0.0285   0.01811   0.00691  -0.0015   1.0000   1.0000
   0.250   0.0284   0.01805   0.00689   0.0024   1.0000   1.0000
   0.500   0.0262   0.01803   0.00689   0.0066   1.0000   1.0000
   0.750   0.0249   0.01806   0.00691   0.0107   1.0000   1.0000
   1.000   0.0271   0.01814   0.00697   0.0142   1.0000   1.0000
   1.250   0.0335   0.01828   0.00709   0.0169   1.0000   1.0000
   1.500   0.0659   0.01851   0.00739   0.0146   0.9921   1.0000
   1.750   0.1042   0.01876   0.00774   0.0113   0.9812   1.0000
   2.000   0.1429   0.01901   0.00816   0.0081   0.9699   1.0000
   2.250   0.1825   0.01927   0.00859   0.0049   0.9579   1.0000
   2.500   0.2233   0.01951   0.00906   0.0016   0.9452   1.0000
   2.750   0.2651   0.01974   0.00964  -0.0018   0.9318   1.0000
   3.000   0.3079   0.01993   0.01019  -0.0051   0.9177   1.0000
   3.250   0.4303   0.01779   0.00871  -0.0150   0.7435   1.0000
   3.500   0.4298   0.01986   0.00809  -0.0069   0.2146   1.0000
   3.750   0.4399   0.02200   0.00942  -0.0046   0.1029   1.0000
   4.000   0.4560   0.02323   0.01057  -0.0028   0.0800   1.0000
   4.250   0.4725   0.02449   0.01186  -0.0009   0.0716   1.0000
   4.500   0.4921   0.02565   0.01326   0.0009   0.0660   1.0000
   4.750   0.5135   0.02719   0.01479   0.0020   0.0588   1.0000
   5.000   0.5389   0.02849   0.01635   0.0030   0.0525   1.0000
   5.250   0.5664   0.03033   0.01847   0.0036   0.0498   1.0000
   5.500   0.5924   0.03246   0.02080   0.0042   0.0479   1.0000
   5.750   0.6162   0.03493   0.02352   0.0051   0.0467   1.0000
   6.000   0.6366   0.03789   0.02674   0.0062   0.0452   1.0000
   6.250   0.6543   0.03994   0.02940   0.0083   0.0432   1.0000
   6.500   0.6700   0.04246   0.03245   0.0103   0.0411   1.0000
   6.750   0.6836   0.04541   0.03586   0.0123   0.0406   1.0000
   7.000   0.6949   0.04864   0.03952   0.0142   0.0407   1.0000
   7.250   0.7036   0.05206   0.04335   0.0162   0.0410   1.0000
   7.500   0.7099   0.05565   0.04731   0.0180   0.0414   1.0000
   7.750   0.7137   0.05939   0.05146   0.0197   0.0419   1.0000
   8.000   0.7152   0.06324   0.05558   0.0210   0.0424   1.0000
   8.250   0.7146   0.06717   0.05974   0.0222   0.0430   1.0000
   8.500   0.7122   0.07118   0.06391   0.0230   0.0436   1.0000
   8.750   0.7093   0.07527   0.06811   0.0235   0.0443   1.0000
   9.000   0.7101   0.07963   0.07250   0.0239   0.0450   1.0000
   9.250   0.6928   0.08315   0.07627   0.0238   0.0468   1.0000
   9.500   0.6691   0.08897   0.08215   0.0197   0.0486   1.0000
   9.750   0.6568   0.09590   0.08898   0.0138   0.0505   1.0000
  10.000   0.6516   0.10210   0.09513   0.0094   0.0526   1.0000
  10.250   0.6501   0.10733   0.10031   0.0069   0.0549   1.0000
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