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EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/7.0 (eh2070-il)
Reynolds number: 100,000
Max Cl/Cd: 45.84 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2070-il-100000-n5.txt
Download as CSV file: xf-eh2070-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/7.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5322   0.09104   0.08655   0.0072   1.0000   0.0372
  -7.500  -0.5327   0.08731   0.08288   0.0046   1.0000   0.0376
  -7.250  -0.5313   0.08339   0.07899   0.0015   1.0000   0.0381
  -7.000  -0.5267   0.07929   0.07489  -0.0015   1.0000   0.0385
  -6.750  -0.5203   0.07508   0.07066  -0.0042   1.0000   0.0387
  -6.500  -0.5074   0.07169   0.06697  -0.0107   1.0000   0.0427
  -6.250  -0.4600   0.05450   0.05028  -0.0096   1.0000   0.0264
  -6.000  -0.4529   0.04939   0.04507  -0.0111   1.0000   0.0246
  -5.750  -0.4438   0.04400   0.03954  -0.0125   1.0000   0.0228
  -5.500  -0.4316   0.03807   0.03333  -0.0136   1.0000   0.0209
  -5.250  -0.4158   0.03266   0.02757  -0.0140   1.0000   0.0198
  -5.000  -0.4202   0.04140   0.03558  -0.0130   1.0000   0.0199
  -4.750  -0.4031   0.03985   0.03399  -0.0130   1.0000   0.0237
  -4.500  -0.3820   0.03643   0.03023  -0.0125   1.0000   0.0252
  -4.250  -0.3603   0.03274   0.02614  -0.0116   1.0000   0.0244
  -4.000  -0.3375   0.02934   0.02227  -0.0105   1.0000   0.0238
  -3.750  -0.3137   0.02634   0.01879  -0.0094   1.0000   0.0234
  -3.500  -0.2891   0.02378   0.01577  -0.0083   1.0000   0.0233
  -3.250  -0.2640   0.02161   0.01322  -0.0072   1.0000   0.0234
  -3.000  -0.2390   0.01982   0.01107  -0.0062   1.0000   0.0239
  -2.750  -0.2147   0.01832   0.00939  -0.0052   1.0000   0.0249
  -2.500  -0.1842   0.01693   0.00785  -0.0056   0.9855   0.0270
  -2.250  -0.1463   0.01574   0.00656  -0.0076   0.9513   0.0334
  -2.000  -0.1093   0.01480   0.00556  -0.0093   0.9159   0.0497
  -1.750  -0.0769   0.01388   0.00481  -0.0099   0.8804   0.1065
  -1.500  -0.0519   0.01246   0.00428  -0.0097   0.8471   0.3390
  -1.250   0.0277   0.01110   0.00435  -0.0165   0.8247   0.9777
  -1.000   0.0814   0.01108   0.00389  -0.0216   0.7921   1.0000
  -0.750   0.1036   0.01114   0.00367  -0.0203   0.7627   1.0000
  -0.500   0.1260   0.01121   0.00348  -0.0192   0.7375   1.0000
  -0.250   0.1486   0.01129   0.00331  -0.0180   0.7149   1.0000
   0.000   0.1717   0.01138   0.00320  -0.0171   0.6939   1.0000
   0.250   0.1948   0.01147   0.00311  -0.0161   0.6749   1.0000
   0.500   0.2181   0.01158   0.00306  -0.0152   0.6570   1.0000
   0.750   0.2414   0.01169   0.00303  -0.0143   0.6399   1.0000
   1.000   0.2653   0.01182   0.00304  -0.0135   0.6238   1.0000
   1.250   0.2892   0.01195   0.00305  -0.0127   0.6086   1.0000
   1.500   0.3131   0.01209   0.00310  -0.0119   0.5939   1.0000
   1.750   0.3371   0.01225   0.00316  -0.0112   0.5798   1.0000
   2.000   0.3611   0.01241   0.00325  -0.0105   0.5658   1.0000
   2.250   0.3854   0.01258   0.00342  -0.0098   0.5522   1.0000
   2.500   0.4096   0.01275   0.00355  -0.0091   0.5388   1.0000
   2.750   0.4340   0.01294   0.00372  -0.0084   0.5258   1.0000
   3.000   0.4584   0.01314   0.00391  -0.0077   0.5128   1.0000
   3.250   0.4829   0.01334   0.00413  -0.0071   0.4998   1.0000
   3.500   0.5074   0.01355   0.00437  -0.0065   0.4868   1.0000
   3.750   0.5321   0.01378   0.00472  -0.0059   0.4738   1.0000
   4.000   0.5568   0.01401   0.00502  -0.0053   0.4608   1.0000
   4.250   0.5815   0.01426   0.00534  -0.0047   0.4479   1.0000
   4.500   0.6064   0.01453   0.00571  -0.0042   0.4353   1.0000
   4.750   0.6313   0.01481   0.00611  -0.0036   0.4226   1.0000
   5.000   0.6561   0.01510   0.00653  -0.0030   0.4092   1.0000
   5.250   0.6809   0.01539   0.00698  -0.0024   0.3946   1.0000
   5.500   0.7054   0.01568   0.00755  -0.0018   0.3774   1.0000
   5.750   0.7266   0.01585   0.00756  -0.0007   0.3021   1.0000
   6.000   0.7406   0.01779   0.00832   0.0002   0.1026   1.0000
   6.250   0.7557   0.02022   0.01022   0.0013   0.0302   1.0000
   6.500   0.7757   0.02165   0.01190   0.0024   0.0246   1.0000
   6.750   0.7948   0.02307   0.01360   0.0035   0.0218   1.0000
   7.000   0.8103   0.02487   0.01556   0.0047   0.0182   1.0000
   7.250   0.8275   0.02641   0.01727   0.0059   0.0158   1.0000
   7.500   0.8445   0.02816   0.01918   0.0073   0.0150   1.0000
   7.750   0.8625   0.03013   0.02142   0.0087   0.0144   1.0000
   8.000   0.8810   0.03238   0.02388   0.0099   0.0140   1.0000
   8.250   0.8992   0.03492   0.02668   0.0111   0.0137   1.0000
   8.500   0.9155   0.03772   0.02983   0.0123   0.0135   1.0000
   8.750   0.9287   0.04078   0.03327   0.0134   0.0134   1.0000
   9.000   0.9376   0.04414   0.03705   0.0146   0.0133   1.0000
   9.250   0.9420   0.04762   0.04093   0.0158   0.0134   1.0000
   9.500   0.9413   0.05125   0.04493   0.0168   0.0134   1.0000
   9.750   0.9356   0.05484   0.04884   0.0176   0.0135   1.0000
  10.000   0.9231   0.05828   0.05251   0.0184   0.0135   1.0000
  10.250   0.9089   0.06215   0.05658   0.0176   0.0136   1.0000
  10.500   0.8941   0.06678   0.06139   0.0150   0.0137   1.0000
  10.750   0.8793   0.07212   0.06688   0.0114   0.0138   1.0000
  11.000   0.8627   0.07853   0.07344   0.0066   0.0139   1.0000
  11.250   0.8483   0.08520   0.08020   0.0016   0.0140   1.0000
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