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dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: dh4009sm (dh4009sm-il)
Reynolds number: 500,000
Max Cl/Cd: 42.09 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dh4009sm-il-500000-n5.txt
Download as CSV file: xf-dh4009sm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6452   0.08133   0.07898  -0.0206   1.0000   0.0087
  -9.000  -0.6570   0.07675   0.07435  -0.0226   1.0000   0.0087
  -8.750  -0.6706   0.07312   0.07067  -0.0221   1.0000   0.0087
  -8.500  -0.6788   0.06928   0.06673  -0.0212   1.0000   0.0087
  -8.250  -0.6829   0.06534   0.06268  -0.0203   1.0000   0.0087
  -8.000  -0.6843   0.06144   0.05865  -0.0190   1.0000   0.0087
  -7.750  -0.6830   0.05763   0.05468  -0.0176   1.0000   0.0087
  -7.500  -0.6792   0.05392   0.05081  -0.0159   1.0000   0.0087
  -5.750  -0.6149   0.02994   0.02528  -0.0015   1.0000   0.0080
  -5.500  -0.5998   0.02719   0.02225   0.0006   1.0000   0.0077
  -5.250  -0.5818   0.02462   0.01941   0.0026   0.9999   0.0074
  -5.000  -0.5516   0.02181   0.01628   0.0021   0.9981   0.0072
  -4.750  -0.5211   0.01931   0.01347   0.0018   0.9955   0.0071
  -4.500  -0.4946   0.01729   0.01122   0.0023   0.9868   0.0071
  -4.250  -0.4665   0.01563   0.00936   0.0025   0.9784   0.0074
  -4.000  -0.4363   0.01438   0.00797   0.0020   0.9721   0.0079
  -3.750  -0.4041   0.01344   0.00694   0.0009   0.9666   0.0084
  -3.500  -0.3715   0.01273   0.00616  -0.0003   0.9597   0.0087
  -3.250  -0.3387   0.01150   0.00488  -0.0019   0.9541   0.0100
  -3.000  -0.3035   0.01075   0.00405  -0.0038   0.9468   0.0103
  -2.750  -0.2646   0.01009   0.00332  -0.0066   0.9407   0.0105
  -2.500  -0.2243   0.00958   0.00274  -0.0097   0.9330   0.0109
  -2.250  -0.1827   0.00919   0.00228  -0.0131   0.9249   0.0120
  -2.000  -0.1431   0.00893   0.00191  -0.0160   0.9140   0.0145
  -1.750  -0.1073   0.00863   0.00165  -0.0181   0.9017   0.0409
  -1.250  -0.0760   0.00588   0.00127  -0.0143   0.8714   0.7269
  -1.000  -0.0491   0.00586   0.00127  -0.0141   0.8601   0.7525
  -0.750  -0.0210   0.00587   0.00123  -0.0142   0.8498   0.7602
  -0.500   0.0069   0.00589   0.00120  -0.0143   0.8401   0.7664
  -0.250   0.0343   0.00591   0.00119  -0.0142   0.8298   0.7731
   0.000   0.0610   0.00594   0.00118  -0.0140   0.8166   0.7796
   0.250   0.0874   0.00598   0.00118  -0.0137   0.8021   0.7862
   0.500   0.1137   0.00601   0.00119  -0.0134   0.7896   0.7929
   0.750   0.1402   0.00603   0.00123  -0.0131   0.7793   0.7996
   1.000   0.1668   0.00606   0.00126  -0.0129   0.7694   0.8063
   1.250   0.1924   0.00610   0.00131  -0.0124   0.7525   0.8132
   1.500   0.2163   0.00619   0.00133  -0.0115   0.7217   0.8203
   1.750   0.2387   0.00633   0.00135  -0.0102   0.6764   0.8275
   2.000   0.2573   0.00666   0.00137  -0.0081   0.5817   0.8352
   2.250   0.2699   0.00759   0.00155  -0.0052   0.3874   0.8438
   2.500   0.2866   0.00849   0.00184  -0.0034   0.2147   0.8520
   2.750   0.3053   0.00929   0.00215  -0.0019   0.0752   0.8609
   3.000   0.3291   0.00962   0.00239  -0.0012   0.0414   0.8693
   3.250   0.3539   0.00984   0.00262  -0.0007   0.0297   0.8780
   3.500   0.3781   0.01015   0.00295   0.0000   0.0220   0.8876
   3.750   0.4037   0.01033   0.00321   0.0004   0.0190   0.8969
   4.000   0.4288   0.01060   0.00353   0.0008   0.0160   0.9071
   4.250   0.4522   0.01115   0.00419   0.0017   0.0136   0.9184
   4.500   0.4783   0.01151   0.00463   0.0019   0.0128   0.9302
   4.750   0.5055   0.01202   0.00525   0.0018   0.0118   0.9418
   5.000   0.5346   0.01270   0.00604   0.0013   0.0110   0.9521
   5.250   0.5645   0.01353   0.00698   0.0005   0.0105   0.9617
   5.750   0.6266   0.01516   0.00879  -0.0016   0.0094   0.9782
   6.000   0.6567   0.01600   0.00971  -0.0027   0.0087   0.9862
   6.250   0.6838   0.01807   0.01202  -0.0030   0.0083   0.9933
   6.500   0.7117   0.01968   0.01389  -0.0034   0.0080   1.0000
   6.750   0.7299   0.02095   0.01538  -0.0017   0.0078   1.0000
   7.000   0.7465   0.02278   0.01749   0.0003   0.0075   1.0000
   7.250   0.7599   0.02556   0.02065   0.0030   0.0072   1.0000
   7.500   0.7676   0.02978   0.02536   0.0065   0.0070   1.0000
   7.750   0.7713   0.03475   0.03079   0.0104   0.0069   1.0000
   8.000   0.7738   0.03956   0.03598   0.0137   0.0069   1.0000
   8.250   0.7761   0.04410   0.04083   0.0165   0.0066   1.0000
   8.500   0.7773   0.04842   0.04541   0.0188   0.0063   1.0000
   8.750   0.7755   0.05277   0.04998   0.0208   0.0061   1.0000
   9.000   0.7685   0.05751   0.05492   0.0225   0.0061   1.0000
   9.250   0.7575   0.06224   0.05981   0.0237   0.0060   1.0000
   9.500   0.7395   0.06671   0.06440   0.0248   0.0061   1.0000
   9.750   0.7198   0.07220   0.06999   0.0227   0.0061   1.0000
  10.000   0.7008   0.08083   0.07868   0.0148   0.0063   1.0000
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