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EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EH 2.0/7.0 (eh2070-il)
Reynolds number: 100,000
Max Cl/Cd: 46.62 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh2070-il-100000.txt
Download as CSV file: xf-eh2070-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4609   0.08883   0.08470   0.0049   1.0000   0.0698
  -7.750  -0.4705   0.08546   0.08139   0.0009   1.0000   0.0706
  -7.500  -0.4817   0.08193   0.07791  -0.0034   1.0000   0.0709
  -7.250  -0.4890   0.07827   0.07418  -0.0078   1.0000   0.0713
  -7.000  -0.4739   0.07145   0.06749  -0.0041   1.0000   0.0736
  -6.750  -0.4661   0.06737   0.06343  -0.0033   1.0000   0.0777
  -6.500  -0.5187   0.07296   0.06859  -0.0070   1.0000   0.0741
  -6.250  -0.5077   0.06933   0.06495  -0.0072   1.0000   0.0781
  -6.000  -0.4946   0.06791   0.06299  -0.0130   1.0000   0.0848
  -5.750  -0.4843   0.06147   0.05684  -0.0110   1.0000   0.0887
  -5.500  -0.4686   0.05890   0.05386  -0.0137   1.0000   0.0991
  -5.250  -0.4552   0.05449   0.04968  -0.0123   1.0000   0.1062
  -5.000  -0.4109   0.03670   0.03225  -0.0131   1.0000   0.1199
  -4.750  -0.3965   0.03273   0.02816  -0.0135   1.0000   0.1310
  -4.500  -0.4042   0.04441   0.03913  -0.0132   1.0000   0.1425
  -4.250  -0.3861   0.04138   0.03603  -0.0128   1.0000   0.1582
  -4.000  -0.3684   0.03866   0.03316  -0.0123   1.0000   0.1832
  -3.750  -0.3511   0.03594   0.03042  -0.0113   1.0000   0.2111
  -3.500  -0.2957   0.02978   0.02233  -0.0103   1.0000   0.0708
  -3.250  -0.2698   0.02602   0.01800  -0.0088   1.0000   0.0589
  -3.000  -0.2449   0.02364   0.01535  -0.0077   1.0000   0.0571
  -2.750  -0.2219   0.02146   0.01305  -0.0069   1.0000   0.0627
  -2.500  -0.1973   0.01968   0.01099  -0.0057   1.0000   0.0643
  -2.250  -0.1737   0.01811   0.00926  -0.0043   1.0000   0.0673
  -2.000  -0.1531   0.01677   0.00785  -0.0027   1.0000   0.0727
  -1.750  -0.0212   0.01094   0.00518  -0.0186   1.0000   1.0000
  -1.500  -0.0010   0.01088   0.00483  -0.0177   1.0000   1.0000
  -1.250   0.0138   0.01093   0.00476  -0.0162   1.0000   1.0000
  -1.000   0.0411   0.01114   0.00482  -0.0179   0.9842   1.0000
  -0.750   0.1061   0.01113   0.00452  -0.0256   0.9470   1.0000
  -0.500   0.1553   0.01111   0.00423  -0.0297   0.9054   1.0000
  -0.250   0.1823   0.01123   0.00411  -0.0290   0.8663   1.0000
   0.000   0.2027   0.01140   0.00407  -0.0271   0.8343   1.0000
   0.250   0.2228   0.01160   0.00407  -0.0251   0.8068   1.0000
   0.500   0.2433   0.01181   0.00411  -0.0234   0.7817   1.0000
   0.750   0.2648   0.01203   0.00418  -0.0219   0.7591   1.0000
   1.000   0.2864   0.01225   0.00425  -0.0204   0.7390   1.0000
   1.250   0.3087   0.01249   0.00437  -0.0192   0.7189   1.0000
   1.500   0.3312   0.01273   0.00450  -0.0180   0.7005   1.0000
   1.750   0.3538   0.01298   0.00464  -0.0168   0.6838   1.0000
   2.000   0.3771   0.01324   0.00485  -0.0159   0.6661   1.0000
   2.250   0.4005   0.01351   0.00510  -0.0149   0.6494   1.0000
   2.500   0.4239   0.01379   0.00532  -0.0140   0.6336   1.0000
   2.750   0.4475   0.01407   0.00557  -0.0131   0.6184   1.0000
   3.000   0.4713   0.01436   0.00583  -0.0121   0.6036   1.0000
   3.250   0.4951   0.01466   0.00612  -0.0113   0.5890   1.0000
   3.500   0.5192   0.01498   0.00651  -0.0105   0.5742   1.0000
   3.750   0.5434   0.01530   0.00689  -0.0097   0.5590   1.0000
   4.000   0.5677   0.01564   0.00730  -0.0090   0.5442   1.0000
   4.250   0.5921   0.01600   0.00773  -0.0083   0.5297   1.0000
   4.500   0.6166   0.01637   0.00820  -0.0076   0.5153   1.0000
   4.750   0.6411   0.01675   0.00876  -0.0068   0.5005   1.0000
   5.000   0.6656   0.01711   0.00925  -0.0061   0.4852   1.0000
   5.250   0.6901   0.01745   0.00972  -0.0053   0.4696   1.0000
   5.500   0.7146   0.01772   0.01009  -0.0043   0.4530   1.0000
   5.750   0.7341   0.01667   0.00898  -0.0018   0.4004   1.0000
   6.000   0.7529   0.01615   0.00837   0.0002   0.2960   1.0000
   6.250   0.7596   0.01993   0.01045   0.0021   0.0607   1.0000
   6.500   0.7778   0.02173   0.01245   0.0035   0.0500   1.0000
   6.750   0.7938   0.02363   0.01442   0.0051   0.0450   1.0000
   7.000   0.8119   0.02561   0.01643   0.0068   0.0420   1.0000
   7.250   0.8331   0.02730   0.01822   0.0081   0.0380   1.0000
   7.500   0.8549   0.02945   0.02046   0.0092   0.0359   1.0000
   7.750   0.8782   0.03209   0.02330   0.0104   0.0359   1.0000
   8.000   0.9003   0.03517   0.02678   0.0117   0.0370   1.0000
   8.250   0.9184   0.03873   0.03086   0.0131   0.0388   1.0000
   8.500   0.9326   0.04282   0.03541   0.0144   0.0409   1.0000
   8.750   0.9435   0.04794   0.04084   0.0152   0.0430   1.0000
   9.000   0.9491   0.05137   0.04516   0.0173   0.0489   1.0000
   9.250   0.9502   0.05713   0.05125   0.0179   0.0536   1.0000
   9.500   0.9533   0.06585   0.06029   0.0179   0.0676   1.0000
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