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EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 1.0/9.0 (eh1090-il)
Reynolds number: 200,000
Max Cl/Cd: 54.58 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1090-il-200000-n5.txt
Download as CSV file: xf-eh1090-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6283   0.08704   0.08369  -0.0015   1.0000   0.0124
  -9.500  -0.6370   0.08048   0.07718  -0.0057   1.0000   0.0122
  -9.250  -0.6498   0.07274   0.06949  -0.0121   1.0000   0.0115
  -9.000  -0.6722   0.06420   0.06090  -0.0187   1.0000   0.0111
  -8.750  -0.6911   0.05817   0.05473  -0.0197   1.0000   0.0113
  -8.500  -0.7053   0.05177   0.04809  -0.0200   1.0000   0.0111
  -8.250  -0.7126   0.04603   0.04201  -0.0193   1.0000   0.0112
  -8.000  -0.7120   0.04135   0.03693  -0.0181   1.0000   0.0119
  -7.750  -0.7079   0.03687   0.03199  -0.0166   1.0000   0.0121
  -7.500  -0.6997   0.03279   0.02740  -0.0148   1.0000   0.0122
  -7.250  -0.6868   0.02943   0.02354  -0.0132   1.0000   0.0122
  -7.000  -0.6703   0.02664   0.02030  -0.0117   1.0000   0.0125
  -6.750  -0.6512   0.02438   0.01766  -0.0104   1.0000   0.0127
  -6.500  -0.6305   0.02249   0.01545  -0.0092   1.0000   0.0131
  -6.250  -0.6087   0.02096   0.01364  -0.0081   1.0000   0.0135
  -6.000  -0.5875   0.01933   0.01182  -0.0070   1.0000   0.0141
  -5.750  -0.5670   0.01789   0.01027  -0.0058   1.0000   0.0151
  -5.500  -0.5448   0.01710   0.00942  -0.0049   1.0000   0.0167
  -5.250  -0.5223   0.01643   0.00869  -0.0039   1.0000   0.0190
  -5.000  -0.5006   0.01565   0.00780  -0.0027   1.0000   0.0207
  -4.750  -0.4802   0.01473   0.00680  -0.0013   1.0000   0.0229
  -4.500  -0.4590   0.01406   0.00610  -0.0001   1.0000   0.0273
  -4.250  -0.4378   0.01346   0.00546   0.0011   1.0000   0.0355
  -4.000  -0.4148   0.01293   0.00500   0.0018   0.9986   0.0527
  -3.750  -0.3791   0.01236   0.00456  -0.0001   0.9876   0.0844
  -3.500  -0.3443   0.01183   0.00419  -0.0019   0.9752   0.1239
  -3.250  -0.3104   0.01130   0.00383  -0.0035   0.9606   0.1762
  -3.000  -0.2775   0.01070   0.00351  -0.0050   0.9443   0.2501
  -2.750  -0.2465   0.01005   0.00322  -0.0059   0.9260   0.3497
  -2.500  -0.2196   0.00934   0.00300  -0.0059   0.9048   0.4783
  -2.250  -0.1958   0.00875   0.00289  -0.0048   0.8827   0.6112
  -2.000  -0.1714   0.00847   0.00283  -0.0035   0.8601   0.6972
  -1.750  -0.1464   0.00836   0.00278  -0.0022   0.8374   0.7498
  -1.500  -0.1211   0.00833   0.00274  -0.0011   0.8149   0.7897
  -1.250  -0.0958   0.00835   0.00272   0.0001   0.7925   0.8277
  -1.000  -0.0697   0.00840   0.00270   0.0012   0.7707   0.8586
  -0.750  -0.0420   0.00849   0.00268   0.0018   0.7492   0.8824
  -0.500  -0.0126   0.00859   0.00269   0.0020   0.7281   0.9035
  -0.250   0.0192   0.00872   0.00270   0.0017   0.7071   0.9228
   0.000   0.0527   0.00885   0.00270   0.0009   0.6866   0.9379
   0.250   0.0877   0.00896   0.00269  -0.0003   0.6658   0.9480
   0.500   0.1208   0.00906   0.00267  -0.0013   0.6459   0.9570
   0.750   0.1566   0.00915   0.00265  -0.0029   0.6257   0.9628
   1.000   0.1888   0.00925   0.00264  -0.0038   0.6065   0.9697
   1.250   0.2254   0.00932   0.00262  -0.0057   0.5866   0.9743
   1.500   0.2591   0.00942   0.00264  -0.0070   0.5677   0.9805
   1.750   0.2939   0.00950   0.00264  -0.0086   0.5492   0.9854
   2.000   0.3287   0.00958   0.00266  -0.0102   0.5301   0.9904
   2.250   0.3626   0.00968   0.00269  -0.0116   0.5115   0.9953
   2.500   0.3974   0.00976   0.00276  -0.0133   0.4927   1.0000
   2.750   0.4203   0.00987   0.00283  -0.0124   0.4761   1.0000
   3.000   0.4431   0.01000   0.00292  -0.0115   0.4591   1.0000
   3.250   0.4659   0.01014   0.00303  -0.0106   0.4425   1.0000
   3.500   0.4888   0.01030   0.00319  -0.0097   0.4254   1.0000
   3.750   0.5118   0.01047   0.00334  -0.0089   0.4060   1.0000
   4.000   0.5347   0.01067   0.00351  -0.0080   0.3861   1.0000
   4.250   0.5578   0.01088   0.00370  -0.0071   0.3663   1.0000
   4.500   0.5810   0.01109   0.00392  -0.0063   0.3489   1.0000
   4.750   0.6042   0.01133   0.00420  -0.0055   0.3313   1.0000
   5.000   0.6273   0.01160   0.00446  -0.0047   0.3091   1.0000
   5.250   0.6501   0.01191   0.00475  -0.0038   0.2835   1.0000
   5.500   0.6719   0.01234   0.00506  -0.0029   0.2451   1.0000
   5.750   0.6923   0.01299   0.00544  -0.0019   0.1869   1.0000
   6.000   0.7122   0.01378   0.00595  -0.0010   0.1300   1.0000
   6.250   0.7314   0.01471   0.00663   0.0001   0.0781   1.0000
   6.500   0.7499   0.01580   0.00747   0.0012   0.0364   1.0000
   6.750   0.7702   0.01668   0.00836   0.0023   0.0246   1.0000
   7.000   0.7906   0.01756   0.00933   0.0034   0.0202   1.0000
   7.250   0.8096   0.01862   0.01054   0.0047   0.0180   1.0000
   7.500   0.8300   0.01943   0.01149   0.0057   0.0161   1.0000
   7.750   0.8499   0.02029   0.01245   0.0067   0.0141   1.0000
   8.000   0.8676   0.02141   0.01373   0.0079   0.0130   1.0000
   8.250   0.8824   0.02294   0.01537   0.0094   0.0122   1.0000
   8.500   0.8959   0.02478   0.01733   0.0111   0.0116   1.0000
   8.750   0.9126   0.02622   0.01893   0.0124   0.0112   1.0000
   9.000   0.9286   0.02785   0.02075   0.0137   0.0108   1.0000
   9.250   0.9444   0.02944   0.02254   0.0150   0.0102   1.0000
   9.500   0.9593   0.03088   0.02416   0.0162   0.0094   1.0000
   9.750   0.9725   0.03233   0.02579   0.0174   0.0087   1.0000
  10.000   0.9832   0.03394   0.02757   0.0187   0.0082   1.0000
  10.250   0.9905   0.03600   0.02983   0.0203   0.0080   1.0000
  10.500   0.9934   0.03813   0.03216   0.0222   0.0078   1.0000
  10.750   0.9903   0.04046   0.03472   0.0243   0.0075   1.0000
  11.000   0.9855   0.04310   0.03757   0.0258   0.0075   1.0000
  11.250   0.9778   0.04619   0.04089   0.0265   0.0075   1.0000
  11.500   0.9659   0.05007   0.04499   0.0261   0.0073   1.0000
  11.750   0.9540   0.05433   0.04945   0.0246   0.0073   1.0000
  12.000   0.9430   0.05888   0.05420   0.0224   0.0073   1.0000
  12.250   0.9271   0.06464   0.06016   0.0190   0.0073   1.0000
  12.500   0.9149   0.07031   0.06601   0.0153   0.0073   1.0000
  12.750   0.9036   0.07631   0.07220   0.0111   0.0075   1.0000
  13.000   0.8824   0.08453   0.08055   0.0057   0.0073   1.0000
  13.250   0.8658   0.09288   0.08908   0.0000   0.0076   1.0000
  13.500   0.8375   0.10483   0.10118  -0.0076   0.0078   1.0000
  13.750   0.7786   0.12859   0.12506  -0.0197   0.0085   1.0000
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