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dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: dh4009sm (dh4009sm-il)
Reynolds number: 500,000
Max Cl/Cd: 48.09 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dh4009sm-il-500000.txt
Download as CSV file: xf-dh4009sm-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6509   0.08431   0.08205  -0.0161   1.0000   0.0110
  -9.000  -0.6642   0.07851   0.07622  -0.0206   1.0000   0.0109
  -8.750  -0.6799   0.07432   0.07198  -0.0215   1.0000   0.0109
  -8.500  -0.6902   0.07041   0.06801  -0.0210   1.0000   0.0110
  -8.250  -0.6950   0.06647   0.06397  -0.0205   1.0000   0.0112
  -8.000  -0.6965   0.06262   0.06000  -0.0197   1.0000   0.0115
  -7.750  -0.6949   0.05886   0.05611  -0.0186   1.0000   0.0120
  -7.500  -0.6898   0.05522   0.05230  -0.0173   1.0000   0.0128
  -7.250  -0.6728   0.05288   0.04973  -0.0154   1.0000   0.0143
  -7.000  -0.6577   0.05113   0.04775  -0.0136   1.0000   0.0148
  -6.750  -0.6475   0.04841   0.04481  -0.0116   1.0000   0.0149
  -6.500  -0.6367   0.04576   0.04193  -0.0096   1.0000   0.0150
  -6.250  -0.6253   0.04303   0.03897  -0.0075   1.0000   0.0150
  -6.000  -0.6277   0.03542   0.03099  -0.0044   1.0000   0.0158
  -5.750  -0.6153   0.03237   0.02779  -0.0027   1.0000   0.0164
  -5.500  -0.5999   0.03015   0.02545  -0.0011   1.0000   0.0169
  -5.250  -0.5836   0.02819   0.02333   0.0006   1.0000   0.0176
  -5.000  -0.5665   0.02640   0.02138   0.0023   1.0000   0.0185
  -4.750  -0.5489   0.02476   0.01956   0.0042   1.0000   0.0197
  -4.500  -0.5309   0.02339   0.01798   0.0063   1.0000   0.0212
  -4.250  -0.5122   0.02326   0.01771   0.0085   1.0000   0.0235
  -3.250  -0.3777   0.01438   0.00805   0.0048   0.9915   0.0205
  -3.000  -0.3453   0.01291   0.00649   0.0040   0.9870   0.0192
  -2.750  -0.3119   0.01214   0.00570   0.0027   0.9816   0.0211
  -2.500  -0.2805   0.01106   0.00457   0.0018   0.9756   0.0198
  -2.250  -0.2474   0.01023   0.00367   0.0006   0.9701   0.0192
  -2.000  -0.2126   0.00960   0.00298  -0.0010   0.9654   0.0197
  -1.750  -0.1779   0.00914   0.00243  -0.0026   0.9589   0.0220
  -1.500  -0.1548   0.00614   0.00158  -0.0033   0.9536   0.6332
  -1.250  -0.1240   0.00578   0.00171  -0.0037   0.9450   0.7681
  -1.000  -0.0849   0.00578   0.00180  -0.0060   0.9394   0.8095
  -0.750  -0.0482   0.00578   0.00177  -0.0080   0.9298   0.8223
  -0.500  -0.0111   0.00577   0.00173  -0.0102   0.9201   0.8289
  -0.250   0.0245   0.00578   0.00170  -0.0121   0.9096   0.8352
   0.000   0.0567   0.00580   0.00169  -0.0131   0.8963   0.8418
   0.250   0.0861   0.00583   0.00169  -0.0135   0.8818   0.8487
   0.500   0.1148   0.00587   0.00171  -0.0136   0.8696   0.8555
   0.750   0.1418   0.00590   0.00174  -0.0135   0.8581   0.8627
   1.000   0.1684   0.00593   0.00179  -0.0132   0.8471   0.8700
   1.250   0.1945   0.00596   0.00184  -0.0127   0.8323   0.8774
   1.500   0.2188   0.00601   0.00185  -0.0117   0.8108   0.8854
   1.750   0.2426   0.00605   0.00186  -0.0106   0.7847   0.8930
   2.000   0.2644   0.00612   0.00186  -0.0091   0.7501   0.9022
   2.250   0.2868   0.00622   0.00188  -0.0077   0.7069   0.9104
   2.500   0.3078   0.00640   0.00193  -0.0060   0.6448   0.9196
   2.750   0.3201   0.00713   0.00201  -0.0026   0.4720   0.9312
   3.000   0.3261   0.00906   0.00252   0.0010   0.1121   0.9447
   3.250   0.3518   0.00985   0.00305   0.0012   0.0401   0.9540
   3.500   0.3825   0.01037   0.00361   0.0004   0.0303   0.9614
   3.750   0.4137   0.01086   0.00414  -0.0005   0.0247   0.9689
   4.000   0.4440   0.01199   0.00538  -0.0013   0.0215   0.9745
   4.250   0.4770   0.01277   0.00624  -0.0026   0.0199   0.9794
   4.500   0.5076   0.01393   0.00749  -0.0033   0.0191   0.9847
   4.750   0.5406   0.01555   0.00923  -0.0044   0.0191   0.9879
   5.000   0.5737   0.01720   0.01106  -0.0055   0.0189   0.9916
   5.250   0.6064   0.01880   0.01285  -0.0066   0.0182   0.9952
   5.500   0.6384   0.02180   0.01620  -0.0072   0.0191   0.9981
   6.500   0.6714   0.03753   0.03313   0.0058   0.0220   1.0000
   6.750   0.6802   0.04026   0.03612   0.0087   0.0220   1.0000
   7.000   0.6886   0.04302   0.03913   0.0114   0.0219   1.0000
   7.250   0.6970   0.04567   0.04203   0.0139   0.0218   1.0000
   7.500   0.7214   0.04530   0.04198   0.0160   0.0193   1.0000
   7.750   0.7300   0.04824   0.04514   0.0179   0.0175   1.0000
   8.000   0.7351   0.05143   0.04850   0.0196   0.0167   1.0000
   8.250   0.7380   0.05466   0.05189   0.0211   0.0160   1.0000
   8.500   0.7387   0.05790   0.05526   0.0223   0.0156   1.0000
   8.750   0.7370   0.06114   0.05862   0.0234   0.0152   1.0000
   9.000   0.7316   0.06459   0.06218   0.0243   0.0150   1.0000
   9.250   0.7202   0.06791   0.06557   0.0256   0.0148   1.0000
   9.500   0.7041   0.07242   0.07018   0.0248   0.0149   1.0000
   9.750   0.6866   0.07928   0.07713   0.0196   0.0150   1.0000
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