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EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EH 1.5/9.0 (eh1590-il)
Reynolds number: 1,000,000
Max Cl/Cd: 94.66 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh1590-il-1000000.txt
Download as CSV file: xf-eh1590-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.5/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5877   0.08070   0.07922  -0.0046   1.0000   0.0096
  -8.750  -0.6100   0.07220   0.07077  -0.0124   1.0000   0.0091
  -8.500  -0.6314   0.06601   0.06454  -0.0152   1.0000   0.0090
  -8.250  -0.6381   0.06067   0.05913  -0.0171   1.0000   0.0091
  -8.000  -0.6440   0.05442   0.05273  -0.0182   1.0000   0.0092
  -7.750  -0.6884   0.03356   0.03097  -0.0157   1.0000   0.0082
  -7.500  -0.6794   0.02985   0.02693  -0.0140   1.0000   0.0082
  -7.250  -0.6675   0.02658   0.02333  -0.0123   1.0000   0.0081
  -7.000  -0.6507   0.02430   0.02078  -0.0110   1.0000   0.0081
  -6.750  -0.6335   0.02197   0.01817  -0.0096   1.0000   0.0081
  -6.500  -0.6146   0.01995   0.01589  -0.0082   1.0000   0.0080
  -6.250  -0.5976   0.01715   0.01271  -0.0065   1.0000   0.0081
  -6.000  -0.5780   0.01516   0.01047  -0.0050   1.0000   0.0082
  -5.750  -0.5570   0.01381   0.00895  -0.0036   1.0000   0.0083
  -5.500  -0.5358   0.01253   0.00753  -0.0023   0.9997   0.0083
  -5.250  -0.5026   0.01104   0.00587  -0.0036   0.9913   0.0089
  -5.000  -0.4667   0.01033   0.00510  -0.0054   0.9809   0.0097
  -4.750  -0.4315   0.00986   0.00459  -0.0070   0.9625   0.0107
  -4.500  -0.4012   0.00944   0.00404  -0.0074   0.9328   0.0114
  -4.250  -0.3772   0.00916   0.00362  -0.0063   0.8980   0.0120
  -4.000  -0.3529   0.00896   0.00327  -0.0053   0.8654   0.0125
  -3.750  -0.3288   0.00856   0.00268  -0.0043   0.8353   0.0152
  -3.500  -0.3038   0.00826   0.00232  -0.0036   0.8076   0.0259
  -3.250  -0.2782   0.00805   0.00209  -0.0031   0.7821   0.0436
  -3.000  -0.2522   0.00789   0.00191  -0.0027   0.7583   0.0611
  -2.750  -0.2258   0.00776   0.00175  -0.0024   0.7360   0.0790
  -2.500  -0.1994   0.00760   0.00161  -0.0021   0.7149   0.1043
  -2.250  -0.1732   0.00739   0.00148  -0.0018   0.6950   0.1436
  -2.000  -0.1477   0.00708   0.00133  -0.0014   0.6764   0.2127
  -1.750  -0.1227   0.00667   0.00119  -0.0011   0.6588   0.3094
  -1.500  -0.1002   0.00594   0.00103  -0.0004   0.6421   0.4927
  -1.250  -0.0782   0.00533   0.00094   0.0007   0.6263   0.6627
  -1.000  -0.0539   0.00509   0.00091   0.0015   0.6108   0.7463
  -0.750  -0.0281   0.00500   0.00090   0.0021   0.5958   0.7916
  -0.500  -0.0021   0.00496   0.00090   0.0027   0.5813   0.8283
  -0.250   0.0244   0.00496   0.00090   0.0031   0.5671   0.8525
   0.000   0.0510   0.00498   0.00090   0.0036   0.5533   0.8730
   0.250   0.0776   0.00500   0.00092   0.0040   0.5400   0.8904
   0.500   0.1041   0.00504   0.00094   0.0045   0.5269   0.9064
   0.750   0.1300   0.00509   0.00098   0.0051   0.5142   0.9243
   1.000   0.1550   0.00516   0.00104   0.0061   0.5019   0.9435
   1.250   0.1814   0.00527   0.00112   0.0067   0.4897   0.9599
   1.500   0.2095   0.00537   0.00118   0.0069   0.4774   0.9696
   1.750   0.2426   0.00546   0.00121   0.0058   0.4649   0.9727
   2.000   0.2757   0.00556   0.00126   0.0046   0.4520   0.9759
   2.250   0.3079   0.00566   0.00131   0.0036   0.4392   0.9795
   2.750   0.3756   0.00586   0.00142   0.0009   0.4141   0.9839
   3.000   0.4109   0.00595   0.00147  -0.0008   0.4012   0.9853
   3.250   0.4455   0.00605   0.00154  -0.0023   0.3882   0.9871
   3.500   0.4794   0.00616   0.00161  -0.0037   0.3753   0.9893
   3.750   0.5125   0.00627   0.00170  -0.0050   0.3618   0.9916
   4.000   0.5446   0.00640   0.00179  -0.0060   0.3482   0.9940
   4.250   0.5791   0.00652   0.00188  -0.0076   0.3327   0.9954
   4.500   0.6129   0.00668   0.00198  -0.0090   0.3131   0.9971
   4.750   0.6463   0.00688   0.00211  -0.0105   0.2887   0.9989
   5.000   0.6768   0.00715   0.00225  -0.0113   0.2550   1.0000
   5.250   0.6990   0.00741   0.00241  -0.0104   0.2295   1.0000
   5.500   0.7210   0.00769   0.00260  -0.0094   0.2045   1.0000
   5.750   0.7422   0.00810   0.00286  -0.0084   0.1683   1.0000
   6.000   0.7622   0.00869   0.00323  -0.0072   0.1202   1.0000
   6.250   0.7801   0.00957   0.00378  -0.0058   0.0585   1.0000
   6.500   0.7982   0.01049   0.00445  -0.0042   0.0168   1.0000
   6.750   0.8198   0.01099   0.00500  -0.0031   0.0123   1.0000
   7.000   0.8425   0.01133   0.00539  -0.0022   0.0110   1.0000
   7.250   0.8648   0.01176   0.00585  -0.0013   0.0096   1.0000
   7.500   0.8842   0.01264   0.00686   0.0001   0.0079   1.0000
   7.750   0.9054   0.01326   0.00759   0.0011   0.0075   1.0000
   8.000   0.9277   0.01377   0.00815   0.0020   0.0070   1.0000
   8.250   0.9491   0.01440   0.00886   0.0029   0.0065   1.0000
   8.500   0.9701   0.01507   0.00959   0.0038   0.0059   1.0000
   8.750   0.9905   0.01581   0.01039   0.0047   0.0054   1.0000
   9.000   1.0085   0.01681   0.01148   0.0059   0.0051   1.0000
   9.250   1.0180   0.01881   0.01365   0.0082   0.0047   1.0000
   9.500   1.0296   0.02058   0.01557   0.0101   0.0045   1.0000
   9.750   1.0480   0.02141   0.01649   0.0112   0.0044   1.0000
  10.000   1.0625   0.02272   0.01795   0.0127   0.0044   1.0000
  10.250   1.0768   0.02395   0.01929   0.0141   0.0043   1.0000
  10.500   1.0883   0.02543   0.02091   0.0158   0.0042   1.0000
  10.750   1.0981   0.02693   0.02255   0.0175   0.0041   1.0000
  11.000   1.1050   0.02832   0.02407   0.0197   0.0040   1.0000
  11.250   1.1051   0.02991   0.02580   0.0226   0.0040   1.0000
  11.500   1.1017   0.03199   0.02804   0.0250   0.0039   1.0000
  11.750   1.0987   0.03419   0.03040   0.0265   0.0038   1.0000
  12.000   1.0938   0.03684   0.03321   0.0273   0.0038   1.0000
  12.250   1.0858   0.04018   0.03672   0.0274   0.0038   1.0000
  12.500   1.0718   0.04463   0.04138   0.0265   0.0039   1.0000
  12.750   1.0666   0.04818   0.04507   0.0251   0.0038   1.0000
  13.000   1.0511   0.05351   0.05058   0.0227   0.0039   1.0000
  13.250   1.0455   0.05764   0.05483   0.0204   0.0037   1.0000
  13.500   1.0183   0.06553   0.06292   0.0162   0.0040   1.0000
  13.750   1.0136   0.07004   0.06752   0.0133   0.0037   1.0000
  14.000   1.0083   0.07480   0.07237   0.0103   0.0035   1.0000
  14.250   0.9940   0.08144   0.07912   0.0062   0.0034   1.0000
  14.500   0.9692   0.09074   0.08858   0.0006   0.0035   1.0000
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