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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 50,000
Max Cl/Cd: 26.89 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh0009-il-50000-n5.txt
Download as CSV file: xf-eh0009-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6874   0.09384   0.08707  -0.0053   1.0000   0.0378
 -10.250  -0.6985   0.08644   0.07970  -0.0103   1.0000   0.0374
 -10.000  -0.7132   0.07939   0.07265  -0.0155   1.0000   0.0368
  -9.750  -0.7315   0.07320   0.06641  -0.0198   1.0000   0.0364
  -9.500  -0.7500   0.06829   0.06140  -0.0218   1.0000   0.0360
  -9.250  -0.7669   0.06400   0.05695  -0.0219   1.0000   0.0359
  -9.000  -0.7780   0.05959   0.05228  -0.0217   1.0000   0.0358
  -8.750  -0.7837   0.05532   0.04767  -0.0211   1.0000   0.0360
  -8.500  -0.7844   0.05114   0.04307  -0.0201   1.0000   0.0364
  -8.250  -0.7800   0.04727   0.03869  -0.0189   1.0000   0.0377
  -8.000  -0.7712   0.04384   0.03458  -0.0175   1.0000   0.0399
  -7.750  -0.7583   0.04093   0.03157  -0.0166   1.0000   0.0431
  -7.500  -0.7417   0.03826   0.02858  -0.0155   1.0000   0.0460
  -7.250  -0.7219   0.03546   0.02536  -0.0143   1.0000   0.0490
  -7.000  -0.7011   0.03302   0.02250  -0.0131   1.0000   0.0538
  -6.750  -0.6815   0.03127   0.02062  -0.0120   1.0000   0.0624
  -6.500  -0.6610   0.02929   0.01856  -0.0107   1.0000   0.0698
  -6.250  -0.6413   0.02758   0.01675  -0.0094   1.0000   0.0822
  -6.000  -0.6220   0.02599   0.01513  -0.0081   1.0000   0.1040
  -5.750  -0.6041   0.02429   0.01360  -0.0068   1.0000   0.1341
  -5.500  -0.5865   0.02278   0.01242  -0.0057   1.0000   0.1890
  -5.250  -0.5688   0.02153   0.01148  -0.0045   1.0000   0.2567
  -5.000  -0.5507   0.02056   0.01069  -0.0030   1.0000   0.3251
  -4.750  -0.5322   0.01979   0.01011  -0.0014   1.0000   0.3907
  -4.500  -0.5133   0.01918   0.00966   0.0005   1.0000   0.4503
  -4.250  -0.4944   0.01869   0.00928   0.0026   1.0000   0.5050
  -4.000  -0.4750   0.01829   0.00894   0.0047   1.0000   0.5562
  -3.750  -0.4551   0.01797   0.00868   0.0069   1.0000   0.6030
  -3.500  -0.4348   0.01771   0.00844   0.0091   1.0000   0.6471
  -3.250  -0.4141   0.01750   0.00818   0.0113   1.0000   0.6887
  -3.000  -0.3927   0.01735   0.00802   0.0134   1.0000   0.7278
  -2.750  -0.3702   0.01724   0.00786   0.0152   1.0000   0.7651
  -2.500  -0.3458   0.01716   0.00772   0.0167   1.0000   0.8006
  -2.250  -0.3175   0.01712   0.00760   0.0174   1.0000   0.8339
  -2.000  -0.2843   0.01711   0.00744   0.0170   1.0000   0.8653
  -1.750  -0.2459   0.01710   0.00730   0.0153   1.0000   0.8945
  -1.500  -0.2016   0.01709   0.00715   0.0122   1.0000   0.9203
  -1.250  -0.1528   0.01705   0.00694   0.0080   1.0000   0.9434
  -1.000  -0.1005   0.01693   0.00671   0.0028   1.0000   0.9638
  -0.750  -0.0497   0.01675   0.00645  -0.0024   1.0000   0.9839
  -0.500  -0.0062   0.01653   0.00618  -0.0065   1.0000   1.0000
  -0.250  -0.0024   0.01642   0.00609  -0.0034   1.0000   1.0000
   0.000   0.0000   0.01638   0.00605   0.0000   1.0000   1.0000
   0.250   0.0025   0.01642   0.00608   0.0034   1.0000   1.0000
   0.500   0.0062   0.01653   0.00618   0.0065   1.0000   1.0000
   0.750   0.0498   0.01675   0.00645   0.0024   0.9839   1.0000
   1.000   0.1005   0.01693   0.00670  -0.0028   0.9638   1.0000
   1.250   0.1528   0.01705   0.00693  -0.0080   0.9434   1.0000
   1.500   0.2015   0.01709   0.00715  -0.0122   0.9203   1.0000
   1.750   0.2458   0.01710   0.00730  -0.0153   0.8945   1.0000
   2.000   0.2842   0.01711   0.00743  -0.0170   0.8654   1.0000
   2.250   0.3174   0.01712   0.00755  -0.0174   0.8340   1.0000
   2.500   0.3456   0.01715   0.00772  -0.0167   0.8006   1.0000
   2.750   0.3700   0.01723   0.00786  -0.0152   0.7651   1.0000
   3.000   0.3926   0.01735   0.00801  -0.0133   0.7279   1.0000
   3.250   0.4140   0.01750   0.00818  -0.0112   0.6888   1.0000
   3.500   0.4347   0.01771   0.00844  -0.0091   0.6473   1.0000
   3.750   0.4550   0.01796   0.00868  -0.0069   0.6031   1.0000
   4.000   0.4748   0.01829   0.00894  -0.0047   0.5563   1.0000
   4.250   0.4943   0.01869   0.00927  -0.0026   0.5052   1.0000
   4.500   0.5132   0.01918   0.00966  -0.0005   0.4503   1.0000
   4.750   0.5321   0.01979   0.01011   0.0014   0.3907   1.0000
   5.000   0.5507   0.02055   0.01069   0.0030   0.3252   1.0000
   5.250   0.5688   0.02153   0.01148   0.0045   0.2566   1.0000
   5.500   0.5865   0.02278   0.01242   0.0057   0.1890   1.0000
   5.750   0.6042   0.02428   0.01360   0.0068   0.1340   1.0000
   6.250   0.6414   0.02758   0.01675   0.0094   0.0822   1.0000
   6.500   0.6611   0.02929   0.01856   0.0107   0.0697   1.0000
   6.750   0.6817   0.03128   0.02063   0.0120   0.0623   1.0000
   7.000   0.7012   0.03303   0.02250   0.0130   0.0537   1.0000
   7.250   0.7221   0.03546   0.02536   0.0142   0.0490   1.0000
   7.500   0.7419   0.03826   0.02858   0.0154   0.0460   1.0000
   7.750   0.7585   0.04094   0.03158   0.0165   0.0430   1.0000
   8.000   0.7715   0.04385   0.03459   0.0174   0.0399   1.0000
   8.250   0.7801   0.04730   0.03873   0.0188   0.0376   1.0000
   8.500   0.7846   0.05118   0.04311   0.0200   0.0364   1.0000
   8.750   0.7840   0.05535   0.04770   0.0210   0.0360   1.0000
   9.000   0.7782   0.05966   0.05235   0.0216   0.0358   1.0000
   9.250   0.7672   0.06404   0.05700   0.0218   0.0358   1.0000
   9.500   0.7505   0.06835   0.06146   0.0217   0.0360   1.0000
   9.750   0.7319   0.07330   0.06651   0.0196   0.0363   1.0000
  10.000   0.7139   0.07947   0.07272   0.0153   0.0368   1.0000
  10.250   0.6992   0.08653   0.07979   0.0100   0.0374   1.0000
  10.500   0.6883   0.09394   0.08717   0.0051   0.0379   1.0000
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