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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 500,000
Max Cl/Cd: 59.3 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh0009-il-500000.txt
Download as CSV file: xf-eh0009-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 0.0/9.0                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6899   0.09972   0.09752   0.0041   1.0000   0.0105
 -11.000  -0.7091   0.08966   0.08750  -0.0011   1.0000   0.0102
 -10.750  -0.7395   0.07394   0.07175  -0.0109   1.0000   0.0096
 -10.500  -0.7592   0.06446   0.06215  -0.0194   1.0000   0.0097
 -10.250  -0.7776   0.05812   0.05568  -0.0247   1.0000   0.0097
 -10.000  -0.8017   0.05284   0.05023  -0.0272   1.0000   0.0098
  -9.750  -0.8247   0.04894   0.04617  -0.0261   1.0000   0.0094
  -9.500  -0.8900   0.03679   0.03305  -0.0202   1.0000   0.0072
  -9.250  -0.8830   0.03437   0.03032  -0.0184   1.0000   0.0071
  -9.000  -0.8820   0.03027   0.02580  -0.0161   1.0000   0.0072
  -8.750  -0.8731   0.02710   0.02227  -0.0142   1.0000   0.0072
  -8.500  -0.8614   0.02412   0.01895  -0.0124   1.0000   0.0074
  -8.250  -0.8450   0.02223   0.01689  -0.0111   1.0000   0.0080
  -8.000  -0.8252   0.02100   0.01553  -0.0101   1.0000   0.0085
  -7.750  -0.8048   0.01981   0.01420  -0.0090   1.0000   0.0092
  -7.500  -0.7841   0.01860   0.01284  -0.0079   1.0000   0.0099
  -7.250  -0.7623   0.01767   0.01179  -0.0069   1.0000   0.0108
  -7.000  -0.7390   0.01714   0.01116  -0.0062   1.0000   0.0118
  -6.750  -0.7240   0.01504   0.00891  -0.0042   1.0000   0.0139
  -6.500  -0.7026   0.01427   0.00805  -0.0030   1.0000   0.0154
  -6.250  -0.6812   0.01356   0.00725  -0.0019   1.0000   0.0171
  -6.000  -0.6577   0.01322   0.00687  -0.0010   1.0000   0.0189
  -5.750  -0.6401   0.01198   0.00552   0.0009   1.0000   0.0235
  -5.500  -0.6180   0.01149   0.00497   0.0020   1.0000   0.0284
  -5.250  -0.5970   0.01084   0.00432   0.0033   1.0000   0.0397
  -5.000  -0.5768   0.01017   0.00383   0.0046   1.0000   0.0711
  -4.750  -0.5563   0.00961   0.00347   0.0058   1.0000   0.1130
  -4.500  -0.5357   0.00912   0.00316   0.0070   1.0000   0.1587
  -4.250  -0.5151   0.00869   0.00292   0.0081   1.0000   0.2040
  -4.000  -0.4943   0.00832   0.00272   0.0093   1.0000   0.2489
  -3.750  -0.4736   0.00798   0.00256   0.0104   1.0000   0.2969
  -3.500  -0.4419   0.00764   0.00242   0.0092   0.9975   0.3510
  -3.250  -0.4042   0.00731   0.00228   0.0068   0.9936   0.4100
  -3.000  -0.3684   0.00699   0.00215   0.0049   0.9884   0.4659
  -2.750  -0.3303   0.00674   0.00206   0.0026   0.9839   0.5145
  -2.500  -0.2936   0.00650   0.00197   0.0006   0.9790   0.5606
  -2.250  -0.2574   0.00629   0.00187  -0.0012   0.9731   0.6001
  -2.000  -0.2204   0.00610   0.00180  -0.0031   0.9678   0.6393
  -1.750  -0.1887   0.00592   0.00174  -0.0037   0.9577   0.6727
  -1.500  -0.1578   0.00578   0.00168  -0.0042   0.9467   0.7032
  -1.250  -0.1287   0.00566   0.00163  -0.0041   0.9340   0.7311
  -1.000  -0.1016   0.00556   0.00159  -0.0036   0.9195   0.7578
  -0.750  -0.0757   0.00549   0.00156  -0.0028   0.9034   0.7827
  -0.500  -0.0503   0.00544   0.00154  -0.0019   0.8863   0.8057
  -0.250  -0.0252   0.00541   0.00153  -0.0010   0.8672   0.8272
   0.000   0.0000   0.00540   0.00152   0.0000   0.8475   0.8475
   0.250   0.0251   0.00541   0.00153   0.0010   0.8273   0.8672
   0.500   0.0502   0.00544   0.00154   0.0019   0.8057   0.8863
   0.750   0.0756   0.00549   0.00156   0.0028   0.7828   0.9034
   1.000   0.1015   0.00556   0.00159   0.0037   0.7579   0.9195
   1.250   0.1286   0.00566   0.00162   0.0042   0.7311   0.9340
   1.500   0.1577   0.00578   0.00168   0.0042   0.7030   0.9467
   1.750   0.1887   0.00592   0.00174   0.0037   0.6728   0.9578
   2.000   0.2203   0.00609   0.00180   0.0031   0.6395   0.9679
   2.250   0.2574   0.00629   0.00187   0.0012   0.6004   0.9732
   2.500   0.2936   0.00649   0.00197  -0.0006   0.5606   0.9792
   2.750   0.3304   0.00674   0.00206  -0.0026   0.5144   0.9840
   3.000   0.3685   0.00699   0.00215  -0.0049   0.4658   0.9885
   3.250   0.4043   0.00730   0.00227  -0.0068   0.4112   0.9937
   3.500   0.4421   0.00763   0.00241  -0.0093   0.3516   0.9977
   3.750   0.4732   0.00798   0.00256  -0.0103   0.2970   1.0000
   4.000   0.4938   0.00833   0.00272  -0.0092   0.2477   1.0000
   4.250   0.5147   0.00868   0.00292  -0.0080   0.2044   1.0000
   4.500   0.5353   0.00911   0.00316  -0.0069   0.1591   1.0000
   4.750   0.5559   0.00961   0.00347  -0.0057   0.1134   1.0000
   5.000   0.5764   0.01016   0.00382  -0.0045   0.0715   1.0000
   5.250   0.5967   0.01084   0.00432  -0.0032   0.0397   1.0000
   5.500   0.6177   0.01149   0.00496  -0.0019   0.0284   1.0000
   5.750   0.6399   0.01198   0.00551  -0.0008   0.0236   1.0000
   6.000   0.6576   0.01322   0.00686   0.0010   0.0189   1.0000
   6.250   0.6809   0.01357   0.00726   0.0019   0.0171   1.0000
   6.500   0.7025   0.01428   0.00805   0.0031   0.0154   1.0000
   6.750   0.7239   0.01504   0.00891   0.0042   0.0139   1.0000
   7.000   0.7401   0.01692   0.01093   0.0060   0.0120   1.0000
   7.250   0.7620   0.01780   0.01193   0.0070   0.0109   1.0000
   7.500   0.7844   0.01857   0.01281   0.0079   0.0099   1.0000
   7.750   0.8051   0.01979   0.01417   0.0090   0.0092   1.0000
   8.000   0.8251   0.02117   0.01572   0.0101   0.0087   1.0000
   8.250   0.8448   0.02242   0.01711   0.0111   0.0081   1.0000
   8.500   0.8623   0.02403   0.01886   0.0123   0.0075   1.0000
   8.750   0.8743   0.02695   0.02210   0.0140   0.0072   1.0000
   9.000   0.8801   0.03079   0.02636   0.0162   0.0071   1.0000
   9.250   0.8865   0.03386   0.02977   0.0181   0.0071   1.0000
   9.500   0.8921   0.03658   0.03282   0.0199   0.0073   1.0000
   9.750   0.7912   0.03593   0.03319   0.0268   0.0087   1.0000
  10.000   0.7625   0.04035   0.03781   0.0272   0.0089   1.0000
  10.250   0.7390   0.04538   0.04299   0.0249   0.0090   1.0000
  10.500   0.7166   0.05187   0.04960   0.0206   0.0089   1.0000
  10.750   0.6944   0.06033   0.05818   0.0147   0.0090   1.0000
  11.000   0.6696   0.07147   0.06942   0.0077   0.0090   1.0000
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