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dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: dh4009sm (dh4009sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 53.37 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dh4009sm-il-1000000-n5.txt
Download as CSV file: xf-dh4009sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6851   0.07870   0.07707  -0.0174   1.0000   0.0036
  -9.000  -0.7027   0.07401   0.07233  -0.0192   1.0000   0.0036
  -8.750  -0.7164   0.06978   0.06804  -0.0188   1.0000   0.0036
  -8.500  -0.7234   0.06522   0.06337  -0.0185   1.0000   0.0036
  -8.250  -0.7266   0.06071   0.05874  -0.0177   1.0000   0.0036
  -8.000  -0.7266   0.05627   0.05415  -0.0166   1.0000   0.0038
  -7.750  -0.7235   0.05186   0.04957  -0.0150   1.0000   0.0040
  -7.500  -0.7178   0.04747   0.04498  -0.0130   1.0000   0.0042
  -7.250  -0.7091   0.04347   0.04078  -0.0109   1.0000   0.0044
  -7.000  -0.6985   0.03998   0.03709  -0.0087   1.0000   0.0045
  -6.750  -0.6866   0.03671   0.03362  -0.0065   1.0000   0.0046
  -6.500  -0.6711   0.03408   0.03081  -0.0045   1.0000   0.0048
  -5.750  -0.6065   0.02437   0.02028  -0.0024   0.9970   0.0048
  -5.500  -0.5819   0.02059   0.01612  -0.0019   0.9939   0.0047
  -5.250  -0.5650   0.01781   0.01305   0.0007   0.9761   0.0046
  -5.000  -0.5355   0.01529   0.01024   0.0005   0.9700   0.0047
  -4.750  -0.5031   0.01369   0.00845  -0.0006   0.9642   0.0048
  -4.500  -0.4676   0.01278   0.00742  -0.0026   0.9579   0.0049
  -4.250  -0.4325   0.01093   0.00540  -0.0046   0.9521   0.0057
  -4.000  -0.3913   0.01035   0.00478  -0.0081   0.9451   0.0061
  -3.750  -0.3467   0.00975   0.00413  -0.0123   0.9383   0.0066
  -3.500  -0.3009   0.00916   0.00347  -0.0169   0.9292   0.0069
  -3.250  -0.2582   0.00878   0.00301  -0.0207   0.9159   0.0076
  -3.000  -0.2229   0.00844   0.00258  -0.0227   0.8992   0.0079
  -2.750  -0.1940   0.00815   0.00217  -0.0231   0.8821   0.0080
  -2.500  -0.1673   0.00794   0.00186  -0.0230   0.8673   0.0082
  -2.250  -0.1412   0.00779   0.00162  -0.0227   0.8541   0.0085
  -2.000  -0.1153   0.00764   0.00138  -0.0223   0.8423   0.0102
  -1.750  -0.0894   0.00753   0.00125  -0.0220   0.8314   0.0172
  -1.500  -0.0647   0.00729   0.00114  -0.0215   0.8214   0.0681
  -1.250  -0.0613   0.00521   0.00073  -0.0175   0.8103   0.5811
  -1.000  -0.0408   0.00490   0.00072  -0.0159   0.8005   0.6803
  -0.500   0.0090   0.00485   0.00070  -0.0147   0.7728   0.7235
  -0.250   0.0353   0.00487   0.00068  -0.0144   0.7598   0.7298
   0.250   0.0888   0.00489   0.00068  -0.0141   0.7413   0.7422
   0.750   0.1417   0.00495   0.00071  -0.0136   0.7184   0.7549
   1.000   0.1663   0.00504   0.00072  -0.0129   0.6869   0.7617
   1.250   0.1898   0.00519   0.00075  -0.0120   0.6403   0.7679
   1.500   0.2083   0.00569   0.00081  -0.0101   0.5144   0.7751
   1.750   0.2256   0.00644   0.00099  -0.0082   0.3522   0.7817
   2.000   0.2465   0.00697   0.00115  -0.0071   0.2406   0.7890
   2.250   0.2671   0.00756   0.00136  -0.0059   0.1243   0.7958
   2.500   0.2899   0.00798   0.00156  -0.0051   0.0515   0.8031
   2.750   0.3151   0.00817   0.00170  -0.0046   0.0334   0.8100
   3.000   0.3406   0.00834   0.00185  -0.0043   0.0232   0.8174
   3.250   0.3662   0.00848   0.00202  -0.0039   0.0191   0.8245
   3.500   0.3917   0.00866   0.00220  -0.0036   0.0151   0.8323
   3.750   0.4170   0.00884   0.00245  -0.0031   0.0132   0.8399
   4.000   0.4425   0.00901   0.00267  -0.0028   0.0119   0.8478
   4.250   0.4675   0.00921   0.00291  -0.0023   0.0105   0.8563
   4.500   0.4920   0.00947   0.00322  -0.0017   0.0092   0.8648
   5.000   0.5384   0.01030   0.00429   0.0000   0.0080   0.8845
   5.250   0.5620   0.01065   0.00473   0.0008   0.0078   0.8952
   5.500   0.5860   0.01098   0.00514   0.0014   0.0074   0.9073
   5.750   0.6095   0.01142   0.00569   0.0022   0.0072   0.9208
   6.000   0.6337   0.01196   0.00636   0.0027   0.0070   0.9359
   6.250   0.6611   0.01260   0.00712   0.0025   0.0067   0.9511
   6.500   0.6925   0.01337   0.00802   0.0013   0.0065   0.9637
   6.750   0.7256   0.01413   0.00889  -0.0004   0.0062   0.9738
   7.000   0.7583   0.01489   0.00974  -0.0020   0.0059   0.9825
   7.250   0.7893   0.01557   0.01051  -0.0032   0.0056   0.9911
   7.500   0.8173   0.01627   0.01130  -0.0038   0.0053   0.9995
   7.750   0.8361   0.01738   0.01256  -0.0023   0.0050   1.0000
   8.000   0.8421   0.02122   0.01693   0.0014   0.0047   1.0000
   8.250   0.8594   0.02249   0.01842   0.0030   0.0046   1.0000
   8.500   0.8755   0.02402   0.02015   0.0047   0.0045   1.0000
   8.750   0.8864   0.02669   0.02314   0.0072   0.0043   1.0000
   9.250   0.8276   0.04925   0.04707   0.0202   0.0040   1.0000
   9.500   0.8118   0.05551   0.05357   0.0227   0.0039   1.0000
   9.750   0.7931   0.06089   0.05912   0.0245   0.0039   1.0000
  10.000   0.7703   0.06568   0.06403   0.0255   0.0039   1.0000
  10.250   0.7477   0.07180   0.07024   0.0222   0.0040   1.0000
  10.500   0.7267   0.08257   0.08106   0.0114   0.0041   1.0000
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