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EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 50,000
Max Cl/Cd: 14.62 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh3012-il-50000.txt
Download as CSV file: xf-eh3012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 3.0/12                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3792   0.10056   0.09453  -0.0036   1.0000   0.2423
  -8.250  -0.3882   0.09788   0.09198  -0.0051   1.0000   0.2525
  -8.000  -0.4013   0.09591   0.09015  -0.0064   1.0000   0.2656
  -7.750  -0.3939   0.09248   0.08681  -0.0058   1.0000   0.2812
  -7.500  -0.3640   0.08803   0.08238  -0.0032   1.0000   0.3051
  -7.250  -0.3724   0.08579   0.08030  -0.0027   1.0000   0.3277
  -6.750  -0.3449   0.07964   0.07430   0.0016   1.0000   0.3891
  -6.500  -0.3231   0.07663   0.07138   0.0047   1.0000   0.4321
  -6.000  -0.2357   0.07077   0.06553   0.0135   1.0000   0.6053
  -5.750  -0.1829   0.06683   0.06159   0.0140   1.0000   0.6949
  -5.250  -0.1833   0.06225   0.05738   0.0134   1.0000   0.6940
  -5.000  -0.2392   0.06430   0.05980   0.0204   1.0000   0.6765
  -4.750  -0.3882   0.05264   0.04607  -0.0266   0.9490   0.1869
  -4.500  -0.3438   0.04662   0.03948  -0.0306   0.9355   0.1512
  -4.250  -0.3031   0.04283   0.03510  -0.0337   0.9214   0.1462
  -4.000  -0.2591   0.03951   0.03089  -0.0364   0.9081   0.1414
  -3.750  -0.2136   0.03660   0.02759  -0.0392   0.8954   0.1445
  -3.500  -0.1762   0.03475   0.02523  -0.0403   0.8809   0.1537
  -3.250  -0.1396   0.03281   0.02311  -0.0414   0.8667   0.1647
  -3.000  -0.1028   0.03130   0.02132  -0.0422   0.8527   0.1854
  -2.750   0.1971   0.02340   0.01587  -0.0764   0.8476   1.0000
  -2.500   0.2162   0.02370   0.01581  -0.0752   0.8294   1.0000
  -2.250   0.2348   0.02402   0.01582  -0.0739   0.8129   1.0000
  -2.000   0.2532   0.02437   0.01591  -0.0726   0.7978   1.0000
  -1.750   0.2722   0.02474   0.01603  -0.0714   0.7837   1.0000
  -1.500   0.2911   0.02510   0.01616  -0.0700   0.7710   1.0000
  -1.250   0.3094   0.02559   0.01647  -0.0690   0.7575   1.0000
  -1.000   0.3273   0.02613   0.01686  -0.0680   0.7447   1.0000
  -0.750   0.3452   0.02670   0.01727  -0.0668   0.7329   1.0000
  -0.500   0.3636   0.02714   0.01754  -0.0652   0.7228   1.0000
  -0.250   0.3808   0.02781   0.01811  -0.0642   0.7111   1.0000
   0.000   0.3973   0.02861   0.01881  -0.0632   0.6999   1.0000
   0.250   0.4152   0.02918   0.01925  -0.0616   0.6910   1.0000
   0.500   0.4307   0.03007   0.02007  -0.0605   0.6803   1.0000
   0.750   0.4452   0.03108   0.02102  -0.0594   0.6705   1.0000
   1.000   0.4631   0.03167   0.02149  -0.0577   0.6623   1.0000
   1.250   0.4733   0.03307   0.02288  -0.0566   0.6520   1.0000
   1.500   0.4913   0.03369   0.02340  -0.0548   0.6443   1.0000
   1.750   0.4987   0.03524   0.02496  -0.0534   0.6344   1.0000
   2.000   0.5112   0.03638   0.02604  -0.0518   0.6266   1.0000
   2.250   0.5189   0.03785   0.02749  -0.0500   0.6179   1.0000
   2.500   0.5260   0.03940   0.02901  -0.0482   0.6103   1.0000
   2.750   0.5308   0.04108   0.03067  -0.0463   0.6023   1.0000
   3.000   0.5363   0.04276   0.03231  -0.0444   0.5952   1.0000
   3.250   0.5294   0.04517   0.03470  -0.0421   0.5878   1.0000
   3.500   0.5491   0.04613   0.03560  -0.0407   0.5814   1.0000
   3.750   0.5166   0.04997   0.03942  -0.0375   0.5752   1.0000
   4.000   0.5397   0.05092   0.04033  -0.0365   0.5686   1.0000
   4.250   0.5196   0.05416   0.04352  -0.0339   0.5643   1.0000
   4.500   0.4922   0.05736   0.04664  -0.0305   0.5621   1.0000
   4.750   0.4814   0.06004   0.04928  -0.0287   0.5596   1.0000
   5.000   0.4743   0.06289   0.05209  -0.0276   0.5601   1.0000
   5.250   0.4712   0.06579   0.05499  -0.0271   0.5625   1.0000
   5.500   0.4769   0.06861   0.05780  -0.0271   0.5652   1.0000
   5.750   0.3788   0.07662   0.06586  -0.0300   0.6914   1.0000
   6.000   0.3950   0.07861   0.06784  -0.0298   0.6781   1.0000
   6.250   0.4004   0.08006   0.06927  -0.0286   0.6647   1.0000
   6.500   0.4085   0.08195   0.07115  -0.0278   0.6532   1.0000
   6.750   0.4420   0.08572   0.07494  -0.0298   0.6453   1.0000
   7.000   0.4423   0.08678   0.07600  -0.0282   0.6322   1.0000
   7.250   0.4463   0.08852   0.07773  -0.0273   0.6205   1.0000
   7.500   0.4647   0.09138   0.08061  -0.0277   0.6117   1.0000
   7.750   0.4809   0.09374   0.08300  -0.0278   0.6002   1.0000
   8.000   0.4810   0.09537   0.08465  -0.0268   0.5893   1.0000
   8.250   0.5025   0.09868   0.08798  -0.0275   0.5812   1.0000
   8.500   0.5136   0.10075   0.09008  -0.0272   0.5691   1.0000
   8.750   0.5124   0.10260   0.09195  -0.0265   0.5599   1.0000
   9.000   0.5449   0.10676   0.09618  -0.0279   0.5518   1.0000
   9.250   0.5369   0.10768   0.09713  -0.0266   0.5400   1.0000
   9.500   0.5460   0.11046   0.09995  -0.0267   0.5322   1.0000
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