Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 500,000
Max Cl/Cd: 77.95 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh3012-il-500000-n5.txt
Download as CSV file: xf-eh3012-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -1.0039   0.03561   0.03168  -0.0296   1.0000   0.0003
 -12.000  -1.0044   0.03264   0.02843  -0.0273   1.0000   0.0003
 -11.750  -0.9982   0.03037   0.02591  -0.0253   1.0000   0.0003
 -11.500  -0.9875   0.02857   0.02391  -0.0236   1.0000   0.0003
 -11.250  -0.9747   0.02695   0.02208  -0.0220   1.0000   0.0003
 -11.000  -0.9594   0.02557   0.02053  -0.0205   1.0000   0.0004
 -10.750  -0.9427   0.02433   0.01913  -0.0192   1.0000   0.0004
 -10.500  -0.9242   0.02331   0.01797  -0.0180   1.0000   0.0004
 -10.250  -0.9047   0.02237   0.01690  -0.0169   1.0000   0.0004
 -10.000  -0.8846   0.02150   0.01591  -0.0159   1.0000   0.0004
  -9.750  -0.8638   0.02071   0.01502  -0.0149   1.0000   0.0005
  -9.500  -0.8364   0.01987   0.01407  -0.0153   0.9791   0.0005
  -9.250  -0.7982   0.01907   0.01307  -0.0178   0.9059   0.0005
  -9.000  -0.7777   0.01859   0.01235  -0.0163   0.8535   0.0005
  -8.750  -0.7567   0.01813   0.01168  -0.0150   0.8160   0.0005
  -8.500  -0.7346   0.01768   0.01104  -0.0139   0.7857   0.0005
  -8.250  -0.7118   0.01724   0.01042  -0.0130   0.7599   0.0005
  -8.000  -0.6881   0.01682   0.00985  -0.0123   0.7419   0.0005
  -7.750  -0.6639   0.01642   0.00932  -0.0116   0.7233   0.0005
  -7.500  -0.6394   0.01604   0.00881  -0.0110   0.7082   0.0005
  -7.250  -0.6146   0.01567   0.00833  -0.0104   0.6923   0.0006
  -7.000  -0.5897   0.01534   0.00788  -0.0099   0.6768   0.0006
  -6.250  -0.5053   0.01703   0.00968  -0.0102   0.6321   0.0007
  -6.000  -0.4875   0.01432   0.00653  -0.0081   0.6211   0.0008
  -5.750  -0.4648   0.01334   0.00551  -0.0071   0.6104   0.0074
  -5.500  -0.4391   0.01307   0.00522  -0.0066   0.6006   0.0099
  -5.250  -0.4130   0.01286   0.00494  -0.0063   0.5906   0.0113
  -5.000  -0.3869   0.01264   0.00467  -0.0059   0.5811   0.0118
  -4.750  -0.3609   0.01244   0.00440  -0.0055   0.5715   0.0124
  -4.500  -0.3346   0.01224   0.00417  -0.0051   0.5620   0.0130
  -4.250  -0.3083   0.01207   0.00394  -0.0047   0.5533   0.0137
  -4.000  -0.2819   0.01190   0.00372  -0.0044   0.5443   0.0144
  -3.750  -0.2555   0.01174   0.00351  -0.0041   0.5361   0.0155
  -3.500  -0.2291   0.01157   0.00331  -0.0037   0.5279   0.0174
  -3.250  -0.2027   0.01142   0.00313  -0.0034   0.5201   0.0199
  -3.000  -0.1762   0.01127   0.00295  -0.0031   0.5117   0.0224
  -2.750  -0.1496   0.01113   0.00279  -0.0027   0.5046   0.0254
  -2.500  -0.1231   0.01100   0.00264  -0.0024   0.4971   0.0296
  -2.250  -0.0968   0.01085   0.00251  -0.0021   0.4901   0.0401
  -2.000  -0.0702   0.01072   0.00240  -0.0018   0.4827   0.0516
  -1.750  -0.0437   0.01062   0.00231  -0.0015   0.4762   0.0612
  -1.500  -0.0169   0.01050   0.00222  -0.0013   0.4695   0.0718
  -1.250   0.0096   0.01040   0.00214  -0.0010   0.4624   0.0866
  -1.000   0.0358   0.01024   0.00208  -0.0007   0.4561   0.1161
  -0.750   0.0616   0.01005   0.00203  -0.0004   0.4497   0.1559
  -0.500   0.0863   0.00977   0.00196   0.0001   0.4439   0.2255
  -0.250   0.1069   0.00907   0.00182   0.0012   0.4378   0.3991
   0.000   0.1142   0.00777   0.00176   0.0053   0.4326   0.7498
   0.250   0.1388   0.00770   0.00181   0.0063   0.4272   0.8021
   0.500   0.1652   0.00769   0.00184   0.0068   0.4212   0.8309
   0.750   0.1917   0.00772   0.00188   0.0073   0.4150   0.8551
   1.000   0.2188   0.00775   0.00194   0.0077   0.4095   0.8769
   1.250   0.2465   0.00781   0.00200   0.0079   0.4038   0.8950
   1.750   0.3024   0.00800   0.00211   0.0082   0.3860   0.9220
   2.000   0.3325   0.00814   0.00218   0.0079   0.3709   0.9321
   2.250   0.3634   0.00826   0.00225   0.0073   0.3630   0.9406
   2.500   0.3944   0.00837   0.00232   0.0066   0.3557   0.9459
   2.750   0.4221   0.00847   0.00237   0.0066   0.3493   0.9512
   3.000   0.4541   0.00857   0.00244   0.0057   0.3425   0.9538
   3.250   0.4863   0.00871   0.00252   0.0047   0.3322   0.9563
   3.500   0.5175   0.00887   0.00260   0.0038   0.3189   0.9594
   3.750   0.5473   0.00906   0.00270   0.0032   0.3029   0.9632
   4.000   0.5761   0.00916   0.00279   0.0030   0.2996   0.9672
   4.250   0.6094   0.00930   0.00292   0.0017   0.2935   0.9688
   4.500   0.6426   0.00945   0.00304   0.0003   0.2858   0.9705
   4.750   0.6748   0.00964   0.00318  -0.0008   0.2757   0.9726
   5.000   0.7059   0.00987   0.00334  -0.0018   0.2605   0.9753
   5.250   0.7358   0.01006   0.00351  -0.0024   0.2502   0.9787
   5.500   0.7656   0.01029   0.00369  -0.0031   0.2378   0.9815
   5.750   0.7976   0.01056   0.00390  -0.0044   0.2237   0.9833
   6.000   0.8290   0.01082   0.00413  -0.0055   0.2115   0.9855
   6.250   0.8587   0.01125   0.00444  -0.0064   0.1882   0.9884
   6.500   0.8894   0.01141   0.00463  -0.0072   0.1873   0.9911
   6.750   0.9179   0.01187   0.00499  -0.0080   0.1644   0.9936
   7.000   0.9478   0.01238   0.00540  -0.0091   0.1425   0.9960
   7.250   0.9623   0.01508   0.00736  -0.0092   0.0092   1.0000
   7.500   0.9797   0.01543   0.00772  -0.0075   0.0082   1.0000
   7.750   0.9974   0.01578   0.00810  -0.0060   0.0077   1.0000
   8.250   1.0327   0.01651   0.00890  -0.0029   0.0072   1.0000
   8.500   1.0503   0.01690   0.00933  -0.0014   0.0064   1.0000
   8.750   1.0670   0.01735   0.00982   0.0002   0.0059   1.0000
   9.000   1.0829   0.01786   0.01036   0.0018   0.0057   1.0000
   9.250   1.0993   0.01832   0.01089   0.0034   0.0058   1.0000
   9.500   1.1136   0.01888   0.01150   0.0052   0.0056   1.0000
   9.750   1.1259   0.01952   0.01219   0.0072   0.0054   1.0000
  10.000   1.1342   0.02034   0.01306   0.0097   0.0050   1.0000
  10.250   1.1389   0.02107   0.01386   0.0128   0.0049   1.0000
  10.500   1.1433   0.02189   0.01474   0.0156   0.0049   1.0000
  10.750   1.1494   0.02282   0.01576   0.0176   0.0048   1.0000
  11.000   1.1537   0.02411   0.01714   0.0192   0.0048   1.0000
  11.250   1.1592   0.02554   0.01867   0.0202   0.0043   1.0000
  11.500   1.1635   0.02730   0.02052   0.0207   0.0041   1.0000
  11.750   1.1685   0.02917   0.02247   0.0209   0.0037   1.0000
  12.000   1.1704   0.03149   0.02488   0.0209   0.0039   1.0000
  12.250   1.1725   0.03392   0.02741   0.0207   0.0036   1.0000
  12.750   1.1736   0.03929   0.03302   0.0199   0.0030   1.0000
  13.000   1.1707   0.04242   0.03621   0.0194   0.0034   1.0000
  13.250   1.1646   0.04600   0.03994   0.0187   0.0029   1.0000
  13.500   1.1642   0.04891   0.04290   0.0181   0.0032   1.0000
  13.750   1.1543   0.05302   0.04716   0.0171   0.0028   1.0000
  14.000   1.1466   0.05689   0.05112   0.0162   0.0027   1.0000
  15.000   1.1229   0.07268   0.06726   0.0117   0.0027   1.0000
  15.250   1.1204   0.07630   0.07093   0.0105   0.0026   1.0000
  15.500   1.1140   0.08062   0.07536   0.0091   0.0027   1.0000
  15.750   1.1126   0.08416   0.07895   0.0080   0.0026   1.0000
<< Back to EH 3.0/12 (eh3012-il)

Polar data table (+)

Polar graphs


<< Back to EH 3.0/12 (eh3012-il)