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EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 100,000
Max Cl/Cd: 39.56 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh3012-il-100000.txt
Download as CSV file: xf-eh3012-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4152   0.10732   0.10281  -0.0109   1.0000   0.0933
  -9.250  -0.4348   0.10436   0.09996  -0.0177   1.0000   0.0940
  -9.000  -0.4591   0.10106   0.09673  -0.0234   1.0000   0.0943
  -8.750  -0.4018   0.09517   0.09083  -0.0141   1.0000   0.0977
  -8.500  -0.3943   0.09187   0.08757  -0.0145   1.0000   0.1004
  -8.250  -0.3943   0.08838   0.08415  -0.0165   1.0000   0.1035
  -8.000  -0.4089   0.08440   0.08028  -0.0215   1.0000   0.1066
  -7.750  -0.4428   0.08200   0.07785  -0.0259   1.0000   0.1086
  -7.500  -0.4497   0.07755   0.07339  -0.0271   1.0000   0.1100
  -7.250  -0.4238   0.07321   0.06925  -0.0252   1.0000   0.1128
  -7.000  -0.4168   0.07022   0.06632  -0.0251   1.0000   0.1164
  -6.750  -0.4238   0.06771   0.06381  -0.0258   1.0000   0.1217
  -6.500  -0.4245   0.06403   0.06003  -0.0292   0.9823   0.1262
  -6.250  -0.3928   0.06048   0.05607  -0.0358   0.9547   0.1405
  -6.000  -0.3544   0.05512   0.05095  -0.0384   0.9331   0.1474
  -5.750  -0.3347   0.05159   0.04714  -0.0404   0.9053   0.1598
  -5.500  -0.3225   0.04924   0.04447  -0.0397   0.8798   0.1735
  -5.250  -0.3069   0.04663   0.04179  -0.0381   0.8564   0.1806
  -5.000  -0.2867   0.03588   0.02914  -0.0356   0.8432   0.0779
  -4.750  -0.2690   0.03306   0.02593  -0.0336   0.8254   0.0755
  -4.500  -0.2492   0.03089   0.02328  -0.0316   0.8090   0.0766
  -4.250  -0.2277   0.02888   0.02076  -0.0297   0.7937   0.0778
  -4.000  -0.2042   0.02699   0.01840  -0.0280   0.7794   0.0787
  -3.750  -0.1798   0.02521   0.01628  -0.0267   0.7658   0.0821
  -3.500  -0.1553   0.02423   0.01519  -0.0257   0.7526   0.0891
  -3.250  -0.1284   0.02296   0.01357  -0.0245   0.7403   0.0953
  -3.000  -0.1027   0.02203   0.01260  -0.0237   0.7271   0.1078
  -2.750  -0.0769   0.02102   0.01157  -0.0229   0.7148   0.1251
  -2.500  -0.0527   0.02018   0.01085  -0.0220   0.7038   0.1510
  -2.250  -0.0294   0.01944   0.01019  -0.0208   0.6936   0.1827
  -2.000  -0.0069   0.01875   0.00970  -0.0196   0.6822   0.2209
  -1.750   0.0119   0.01773   0.00914  -0.0178   0.6729   0.2987
  -1.500   0.2346   0.01751   0.01018  -0.0461   0.6512   0.9977
  -1.250   0.2618   0.01748   0.00993  -0.0464   0.6413   1.0000
  -1.000   0.2830   0.01751   0.00977  -0.0455   0.6319   1.0000
  -0.750   0.3048   0.01760   0.00974  -0.0448   0.6220   1.0000
  -0.500   0.3260   0.01766   0.00959  -0.0437   0.6144   1.0000
  -0.250   0.3480   0.01778   0.00964  -0.0431   0.6042   1.0000
   0.000   0.3697   0.01788   0.00958  -0.0422   0.5969   1.0000
   0.250   0.3917   0.01803   0.00968  -0.0415   0.5877   1.0000
   0.500   0.4136   0.01817   0.00968  -0.0406   0.5805   1.0000
   0.750   0.4355   0.01834   0.00979  -0.0399   0.5716   1.0000
   1.000   0.4573   0.01850   0.00985  -0.0390   0.5644   1.0000
   1.250   0.4792   0.01870   0.01000  -0.0382   0.5560   1.0000
   1.500   0.5010   0.01890   0.01010  -0.0372   0.5494   1.0000
   1.750   0.5225   0.01916   0.01037  -0.0364   0.5411   1.0000
   2.000   0.5445   0.01934   0.01040  -0.0354   0.5357   1.0000
   2.250   0.5653   0.01973   0.01087  -0.0346   0.5269   1.0000
   2.500   0.5872   0.01990   0.01091  -0.0335   0.5212   1.0000
   2.750   0.6075   0.02036   0.01145  -0.0327   0.5131   1.0000
   3.000   0.6291   0.02059   0.01161  -0.0316   0.5071   1.0000
   3.250   0.6494   0.02105   0.01211  -0.0306   0.5001   1.0000
   3.500   0.6703   0.02136   0.01241  -0.0295   0.4933   1.0000
   3.750   0.6918   0.02168   0.01266  -0.0284   0.4878   1.0000
   4.000   0.7107   0.02224   0.01333  -0.0273   0.4801   1.0000
   4.250   0.7332   0.02243   0.01342  -0.0262   0.4750   1.0000
   4.500   0.7509   0.02316   0.01428  -0.0251   0.4675   1.0000
   4.750   0.7720   0.02352   0.01463  -0.0239   0.4619   1.0000
   5.000   0.7928   0.02399   0.01510  -0.0228   0.4566   1.0000
   5.250   0.8105   0.02467   0.01591  -0.0216   0.4492   1.0000
   5.500   0.8341   0.02485   0.01601  -0.0206   0.4444   1.0000
   5.750   0.8494   0.02580   0.01713  -0.0192   0.4369   1.0000
   6.000   0.8713   0.02614   0.01748  -0.0182   0.4313   1.0000
   6.250   0.8922   0.02666   0.01801  -0.0171   0.4260   1.0000
   6.500   0.9074   0.02766   0.01919  -0.0157   0.4189   1.0000
   6.750   0.9320   0.02786   0.01934  -0.0149   0.4144   1.0000
   7.000   0.9450   0.02908   0.02077  -0.0134   0.4074   1.0000
   7.250   0.9662   0.02953   0.02126  -0.0124   0.4015   1.0000
   7.500   0.9939   0.02958   0.02123  -0.0118   0.3973   1.0000
   7.750   0.9992   0.03132   0.02328  -0.0098   0.3891   1.0000
   8.000   1.0282   0.03109   0.02301  -0.0093   0.3841   1.0000
   8.250   1.0364   0.03261   0.02475  -0.0074   0.3766   1.0000
   8.500   1.0679   0.03180   0.02386  -0.0069   0.3695   1.0000
   8.750   1.0811   0.03256   0.02479  -0.0053   0.3609   1.0000
   9.000   1.1151   0.03156   0.02367  -0.0050   0.3538   1.0000
   9.250   1.1242   0.03275   0.02509  -0.0031   0.3459   1.0000
   9.500   1.1560   0.03206   0.02433  -0.0028   0.3391   1.0000
   9.750   1.1651   0.03314   0.02565  -0.0009   0.3311   1.0000
  10.000   1.1980   0.03231   0.02474  -0.0007   0.3239   1.0000
  10.250   1.2048   0.03347   0.02615   0.0014   0.3160   1.0000
  10.500   1.2370   0.03280   0.02542   0.0015   0.3091   1.0000
  10.750   1.2427   0.03375   0.02663   0.0038   0.3004   1.0000
  11.000   1.2694   0.03292   0.02576   0.0046   0.2908   1.0000
  11.250   1.2811   0.03337   0.02637   0.0064   0.2825   1.0000
  11.500   1.2930   0.03355   0.02667   0.0084   0.2732   1.0000
  11.750   1.3089   0.03309   0.02620   0.0101   0.2623   1.0000
  12.000   1.3125   0.03335   0.02658   0.0128   0.2517   1.0000
  12.250   1.3037   0.03447   0.02788   0.0164   0.2434   1.0000
  12.500   1.3057   0.03507   0.02851   0.0187   0.2346   1.0000
  12.750   1.2926   0.03710   0.03074   0.0208   0.2260   1.0000
  13.000   1.2836   0.03928   0.03304   0.0218   0.2169   1.0000
  13.250   1.2756   0.04167   0.03548   0.0222   0.2069   1.0000
  13.500   1.2570   0.04570   0.03968   0.0216   0.1971   1.0000
  13.750   1.2374   0.05026   0.04435   0.0205   0.1860   1.0000
  14.000   1.2199   0.05489   0.04904   0.0192   0.1757   1.0000
  14.250   1.1966   0.06051   0.05469   0.0174   0.1634   1.0000
  14.500   1.1726   0.06645   0.06064   0.0153   0.1500   1.0000
  14.750   1.1498   0.07259   0.06676   0.0130   0.1357   1.0000
  15.000   1.1275   0.07886   0.07292   0.0107   0.1199   1.0000
  15.250   1.1049   0.08536   0.07922   0.0082   0.1046   1.0000
  15.500   1.0871   0.09130   0.08501   0.0061   0.0932   1.0000
  15.750   1.0741   0.09665   0.09026   0.0042   0.0842   1.0000
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