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dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: dh4009sm (dh4009sm-il)
Reynolds number: 100,000
Max Cl/Cd: 27.56 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dh4009sm-il-100000.txt
Download as CSV file: xf-dh4009sm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5006   0.12328   0.11833  -0.0107   1.0000   0.0755
 -11.250  -0.5134   0.11992   0.11502  -0.0140   1.0000   0.0763
 -11.000  -0.6327   0.12601   0.12081   0.0008   1.0000   0.0666
 -10.750  -0.6284   0.12221   0.11702   0.0003   1.0000   0.0695
 -10.500  -0.6285   0.11809   0.11293  -0.0017   1.0000   0.0722
 -10.250  -0.6334   0.11365   0.10855  -0.0054   1.0000   0.0747
 -10.000  -0.6439   0.10872   0.10370  -0.0114   1.0000   0.0758
  -9.750  -0.6567   0.10317   0.09821  -0.0179   1.0000   0.0762
  -9.500  -0.6731   0.09873   0.09376  -0.0218   1.0000   0.0763
  -9.250  -0.6401   0.09525   0.09027  -0.0133   1.0000   0.0829
  -9.000  -0.6483   0.09002   0.08509  -0.0174   1.0000   0.0848
  -8.750  -0.6622   0.08535   0.08043  -0.0205   1.0000   0.0860
  -8.500  -0.6787   0.08149   0.07658  -0.0216   1.0000   0.0875
  -8.250  -0.7004   0.07875   0.07361  -0.0223   1.0000   0.0895
  -8.000  -0.6995   0.07333   0.06820  -0.0220   1.0000   0.0922
  -7.750  -0.6894   0.06970   0.06458  -0.0209   1.0000   0.0982
  -7.500  -0.7083   0.06814   0.06245  -0.0197   1.0000   0.1042
  -7.250  -0.6885   0.06256   0.05722  -0.0192   1.0000   0.1116
  -7.000  -0.6874   0.05907   0.05357  -0.0180   1.0000   0.1214
  -6.750  -0.6827   0.05591   0.05029  -0.0166   1.0000   0.1346
  -4.500  -0.5228   0.01432   0.00655  -0.0018   1.0000   0.1331
  -4.250  -0.4998   0.02711   0.01792   0.0004   1.0000   0.0840
  -4.000  -0.4713   0.02515   0.01557   0.0020   1.0000   0.0704
  -3.750  -0.4446   0.02439   0.01436   0.0039   1.0000   0.0627
  -3.500  -0.4180   0.02213   0.01210   0.0046   1.0000   0.0600
  -3.250  -0.3929   0.02064   0.01057   0.0057   1.0000   0.0580
  -3.000  -0.3697   0.01940   0.00929   0.0070   1.0000   0.0572
  -2.750  -0.3494   0.01834   0.00826   0.0086   1.0000   0.0576
  -2.500  -0.3310   0.01747   0.00738   0.0105   1.0000   0.0594
  -2.250  -0.3126   0.01670   0.00653   0.0122   1.0000   0.0654
  -2.000  -0.2932   0.01603   0.00579   0.0137   1.0000   0.0774
  -1.750  -0.1510   0.01613   0.00875   0.0058   1.0000   0.9647
  -1.500  -0.1148   0.01580   0.00825   0.0031   1.0000   0.9728
  -1.250  -0.0737   0.01547   0.00778  -0.0006   1.0000   0.9798
  -1.000  -0.0339   0.01515   0.00735  -0.0041   1.0000   0.9871
  -0.750   0.0069   0.01486   0.00699  -0.0079   1.0000   0.9947
  -0.500   0.0435   0.01456   0.00666  -0.0109   1.0000   1.0000
  -0.250   0.0508   0.01436   0.00651  -0.0083   1.0000   1.0000
   0.000   0.0512   0.01425   0.00645  -0.0047   1.0000   1.0000
   0.250   0.0396   0.01424   0.00648   0.0009   1.0000   1.0000
   0.500   0.0215   0.01424   0.00650   0.0074   1.0000   1.0000
   0.750   0.0069   0.01422   0.00646   0.0133   1.0000   1.0000
   1.000   0.0028   0.01425   0.00647   0.0176   1.0000   1.0000
   1.250   0.0102   0.01440   0.00659   0.0199   1.0000   1.0000
   1.500   0.0238   0.01464   0.00682   0.0211   1.0000   1.0000
   1.750   0.0696   0.01502   0.00728   0.0162   0.9920   1.0000
   2.000   0.1181   0.01535   0.00774   0.0110   0.9821   1.0000
   2.250   0.1653   0.01564   0.00816   0.0062   0.9715   1.0000
   2.500   0.2129   0.01589   0.00860   0.0014   0.9604   1.0000
   2.750   0.2650   0.01605   0.00906  -0.0039   0.9479   1.0000
   3.000   0.4363   0.01583   0.00609  -0.0191   0.1382   1.0000
   3.250   0.4484   0.01712   0.00710  -0.0161   0.0986   1.0000
   3.500   0.4614   0.01810   0.00812  -0.0134   0.0841   1.0000
   3.750   0.4760   0.01903   0.00903  -0.0109   0.0744   1.0000
   4.000   0.4938   0.02053   0.01045  -0.0089   0.0703   1.0000
   4.250   0.5164   0.02191   0.01192  -0.0074   0.0679   1.0000
   4.500   0.5398   0.02342   0.01356  -0.0061   0.0651   1.0000
   4.750   0.5617   0.02543   0.01554  -0.0053   0.0597   1.0000
   5.000   0.5846   0.02748   0.01782  -0.0039   0.0597   1.0000
   5.250   0.6063   0.02923   0.02025  -0.0013   0.0636   1.0000
   5.500   0.6265   0.03229   0.02369   0.0008   0.0691   1.0000
   5.750   0.6477   0.03596   0.02788   0.0033   0.0836   1.0000
   8.500   0.7367   0.07979   0.07479   0.0207   0.1117   1.0000
   8.750   0.7036   0.08262   0.07790   0.0192   0.1104   1.0000
   9.000   0.6785   0.08709   0.08241   0.0160   0.1090   1.0000
   9.250   0.6623   0.09303   0.08830   0.0096   0.1066   1.0000
   9.500   0.6976   0.09526   0.09052   0.0190   0.0981   1.0000
   9.750   0.6756   0.10078   0.09602   0.0123   0.0978   1.0000
  10.000   0.6554   0.10676   0.10190   0.0037   0.0963   1.0000
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