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=100,000 Ncrit=5


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 100,000
Max Cl/Cd: 46.14 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh3012-il-100000-n5.txt
Download as CSV file: xf-eh3012-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3992   0.12613   0.12174  -0.0048   1.0000   0.0536
 -11.250  -0.3994   0.12192   0.11755  -0.0068   1.0000   0.0536
 -10.750  -0.4643   0.11249   0.10770  -0.0046   1.0000   0.0356
 -10.500  -0.4583   0.10887   0.10410  -0.0053   1.0000   0.0346
 -10.250  -0.4569   0.10455   0.09981  -0.0070   1.0000   0.0336
 -10.000  -0.4581   0.09983   0.09514  -0.0093   1.0000   0.0327
  -9.500  -0.4915   0.08295   0.07839  -0.0211   1.0000   0.0295
  -9.250  -0.4979   0.07791   0.07340  -0.0248   1.0000   0.0293
  -9.000  -0.5082   0.07318   0.06868  -0.0272   1.0000   0.0291
  -8.750  -0.5222   0.06872   0.06420  -0.0278   1.0000   0.0290
  -8.500  -0.5335   0.06428   0.05970  -0.0278   1.0000   0.0289
  -8.250  -0.5418   0.05961   0.05491  -0.0275   1.0000   0.0287
  -8.000  -0.5501   0.05428   0.04936  -0.0266   1.0000   0.0286
  -7.750  -0.5549   0.04919   0.04399  -0.0252   1.0000   0.0287
  -7.500  -0.5597   0.04381   0.03815  -0.0229   1.0000   0.0291
  -7.250  -0.5572   0.04006   0.03402  -0.0207   1.0000   0.0301
  -7.000  -0.5341   0.03898   0.03293  -0.0213   0.9775   0.0313
  -6.750  -0.5063   0.03581   0.02932  -0.0230   0.9300   0.0326
  -6.500  -0.4815   0.03205   0.02489  -0.0234   0.8948   0.0334
  -6.250  -0.4583   0.02926   0.02149  -0.0227   0.8636   0.0343
  -6.000  -0.4357   0.02706   0.01873  -0.0216   0.8364   0.0353
  -5.750  -0.4127   0.02538   0.01661  -0.0204   0.8126   0.0365
  -5.500  -0.3900   0.02457   0.01568  -0.0194   0.7909   0.0383
  -5.250  -0.3664   0.02383   0.01472  -0.0184   0.7711   0.0414
  -5.000  -0.3414   0.02276   0.01327  -0.0175   0.7540   0.0441
  -4.750  -0.3175   0.02187   0.01234  -0.0167   0.7376   0.0466
  -4.500  -0.2928   0.02110   0.01143  -0.0159   0.7223   0.0499
  -4.250  -0.2681   0.02037   0.01054  -0.0151   0.7080   0.0551
  -4.000  -0.2436   0.01985   0.00993  -0.0143   0.6945   0.0624
  -3.750  -0.2196   0.01926   0.00928  -0.0134   0.6819   0.0704
  -3.500  -0.1953   0.01878   0.00875  -0.0127   0.6695   0.0821
  -3.250  -0.1707   0.01835   0.00827  -0.0120   0.6576   0.0957
  -3.000  -0.1463   0.01800   0.00788  -0.0112   0.6467   0.1111
  -2.750  -0.1219   0.01769   0.00752  -0.0105   0.6365   0.1290
  -2.500  -0.0974   0.01736   0.00718  -0.0098   0.6255   0.1484
  -2.250  -0.0733   0.01703   0.00681  -0.0089   0.6159   0.1686
  -2.000  -0.0496   0.01664   0.00648  -0.0081   0.6062   0.1990
  -1.750  -0.0268   0.01612   0.00618  -0.0073   0.5969   0.2579
  -1.500  -0.0057   0.01432   0.00644  -0.0048   0.5888   0.7740
  -1.250   0.0292   0.01462   0.00669  -0.0047   0.5787   0.8560
  -1.000   0.0706   0.01502   0.00687  -0.0061   0.5697   0.8950
  -0.750   0.1141   0.01539   0.00706  -0.0082   0.5596   0.9220
  -0.500   0.1741   0.01575   0.00717  -0.0138   0.5492   0.9429
  -0.250   0.2296   0.01597   0.00715  -0.0188   0.5400   0.9617
   0.000   0.2818   0.01605   0.00707  -0.0236   0.5297   0.9767
   0.250   0.3193   0.01603   0.00688  -0.0257   0.5219   0.9837
   0.500   0.3514   0.01600   0.00676  -0.0269   0.5133   0.9876
   0.750   0.3819   0.01601   0.00663  -0.0277   0.5064   0.9916
   1.000   0.4138   0.01599   0.00657  -0.0289   0.4980   0.9953
   1.250   0.4456   0.01599   0.00643  -0.0300   0.4915   0.9991
   1.500   0.4704   0.01605   0.00647  -0.0298   0.4836   1.0000
   1.750   0.4924   0.01612   0.00644  -0.0289   0.4775   1.0000
   2.000   0.5145   0.01621   0.00652  -0.0281   0.4705   1.0000
   2.250   0.5365   0.01631   0.00657  -0.0273   0.4642   1.0000
   2.500   0.5584   0.01642   0.00664  -0.0264   0.4582   1.0000
   2.750   0.5803   0.01656   0.00679  -0.0255   0.4514   1.0000
   3.000   0.6020   0.01669   0.00685  -0.0245   0.4459   1.0000
   3.250   0.6236   0.01687   0.00705  -0.0236   0.4393   1.0000
   3.500   0.6452   0.01703   0.00720  -0.0227   0.4332   1.0000
   3.750   0.6668   0.01721   0.00736  -0.0217   0.4279   1.0000
   4.000   0.6881   0.01743   0.00764  -0.0207   0.4213   1.0000
   4.250   0.7096   0.01763   0.00781  -0.0197   0.4158   1.0000
   4.500   0.7308   0.01787   0.00808  -0.0187   0.4100   1.0000
   4.750   0.7520   0.01812   0.00837  -0.0177   0.4039   1.0000
   5.000   0.7735   0.01834   0.00858  -0.0166   0.3990   1.0000
   5.250   0.7943   0.01864   0.00897  -0.0156   0.3927   1.0000
   5.500   0.8154   0.01891   0.00929  -0.0145   0.3869   1.0000
   5.750   0.8371   0.01917   0.00950  -0.0135   0.3824   1.0000
   6.000   0.8574   0.01954   0.01005  -0.0125   0.3758   1.0000
   6.250   0.8786   0.01982   0.01036  -0.0114   0.3701   1.0000
   6.500   0.8994   0.02013   0.01072  -0.0103   0.3641   1.0000
   6.750   0.9197   0.02045   0.01114  -0.0092   0.3570   1.0000
   7.000   0.9410   0.02070   0.01139  -0.0082   0.3511   1.0000
   7.250   0.9605   0.02111   0.01196  -0.0070   0.3436   1.0000
   7.500   0.9815   0.02137   0.01224  -0.0060   0.3374   1.0000
   7.750   1.0008   0.02180   0.01283  -0.0048   0.3305   1.0000
   8.000   1.0211   0.02217   0.01328  -0.0037   0.3245   1.0000
   8.250   1.0413   0.02257   0.01378  -0.0026   0.3191   1.0000
   8.500   1.0601   0.02308   0.01446  -0.0015   0.3127   1.0000
   8.750   1.0804   0.02344   0.01489  -0.0004   0.3073   1.0000
   9.000   1.0980   0.02397   0.01560   0.0009   0.2999   1.0000
   9.250   1.1165   0.02423   0.01591   0.0022   0.2913   1.0000
   9.500   1.1312   0.02471   0.01658   0.0038   0.2801   1.0000
   9.750   1.1455   0.02516   0.01715   0.0055   0.2683   1.0000
  10.000   1.1579   0.02567   0.01775   0.0073   0.2549   1.0000
  10.250   1.1679   0.02629   0.01846   0.0093   0.2401   1.0000
  10.500   1.1756   0.02708   0.01933   0.0114   0.2250   1.0000
  10.750   1.1793   0.02806   0.02036   0.0138   0.2088   1.0000
  11.000   1.1744   0.02934   0.02162   0.0171   0.1912   1.0000
  11.250   1.1665   0.03110   0.02336   0.0196   0.1743   1.0000
  11.500   1.1561   0.03355   0.02579   0.0211   0.1538   1.0000
  11.750   1.1413   0.03687   0.02904   0.0217   0.1340   1.0000
  12.000   1.1257   0.04076   0.03287   0.0214   0.1159   1.0000
  12.250   1.1036   0.04573   0.03775   0.0205   0.0960   1.0000
  12.500   1.0898   0.05003   0.04206   0.0196   0.0850   1.0000
  12.750   1.0679   0.05549   0.04748   0.0182   0.0695   1.0000
  13.000   1.0482   0.06089   0.05284   0.0166   0.0566   1.0000
  13.250   1.0336   0.06581   0.05780   0.0152   0.0496   1.0000
  13.500   1.0188   0.07092   0.06293   0.0136   0.0430   1.0000
  13.750   1.0029   0.07643   0.06846   0.0117   0.0371   1.0000
  14.000   0.9904   0.08168   0.07378   0.0099   0.0336   1.0000
  14.250   0.9807   0.08663   0.07879   0.0081   0.0313   1.0000
  14.500   0.9704   0.09184   0.08407   0.0062   0.0290   1.0000
<< Back to EH 3.0/12 (eh3012-il)

Polar data table (+)

Polar graphs


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