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EH 2.0/7.0 (eh2070-il)

EH 2.0/7.0 - John Yost EH 2.0/7.0 for tailless R/C aircraft


Airfoil eh2070-il
Details Dat file Parser  
(eh2070-il) EH 2.0/7.0
John Yost EH 2.0/7.0 for tailless R/C aircraft
Max thickness 7% at 28.7% chord.
Max camber 2% at 25.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
EH 2.0/7.0
1.00000 0.00000
0.99901 0.00003
0.99606 0.00014
0.99114 0.00036
0.98429 0.00071
0.97553 0.00121
0.96489 0.00186
0.95241 0.00267
0.93815 0.00362
0.92216 0.00471
0.90451 0.00595
0.88526 0.00737
0.86448 0.00894
0.84227 0.01076
0.81871 0.01262
0.79389 0.01472
0.76791 0.01698
0.74088 0.01941
0.71289 0.02198
0.68406 0.02468
0.65451 0.02749
0.62435 0.03041
0.59369 0.03337
0.56267 0.03634
0.53140 0.03928
0.50000 0.04213
0.46861 0.04484
0.43733 0.04734
0.40631 0.04958
0.37566 0.05150
0.34549 0.05301
0.31549 0.05409
0.28711 0.05467
0.25912 0.05472
0.23209 0.05421
0.20611 0.05312
0.18129 0.05146
0.15773 0.04923
0.13522 0.04647
0.11474 0.04323
0.09549 0.03956
0.07784 0.03554
0.06185 0.03126
0.04759 0.02679
0.03511 0.02224
0.02447 0.01772
0.01571 0.01333
0.00886 0.00926
0.00394 0.00564
0.00099 0.00257
0.00000 0.00000
0.00099 -0.00220
0.00394 -0.00418
0.00886 -0.00600
0.01571 -0.00768
0.02447 -0.00913
0.03511 -0.01031
0.04759 -0.01125
0.06185 -0.01196
0.07784 -0.01247
0.09549 -0.01285
0.11474 -0.01314
0.13552 -0.01336
0.15773 -0.01360
0.18129 -0.01384
0.20611 -0.01412
0.23209 -0.01446
0.25912 -0.01487
0.28711 -0.01533
0.31594 -0.01583
0.34549 -0.01636
0.37566 -0.01689
0.40631 -0.01740
0.43733 -0.01785
0.46861 -0.01822
0.50000 -0.01846
0.53140 -0.01857
0.56267 -0.01851
0.59369 -0.01828
0.62435 -0.01787
0.65451 -0.01729
0.68406 -0.01651
0.71289 -0.01558
0.74088 -0.01452
0.76791 -0.01335
0.79389 -0.01209
0.81871 -0.01078
0.84227 -0.00921
0.86448 -0.00814
0.88526 -0.00687
0.90451 -0.00566
0.92216 -0.00455
0.93815 -0.00354
0.95241 -0.00264
0.96489 -0.00185
0.97553 -0.00120
0.98429 -0.00071
0.99114 -0.00036
0.99606 -0.00014
0.99901 -0.00004
1.00000  0.00000
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Polars for EH 2.0/7.0 (eh2070-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   eh2070-il50,000933.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2070-il50,000533.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2070-il100,000946.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2070-il100,000545.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2070-il200,000960 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2070-il200,000558.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2070-il500,000979.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2070-il500,000575.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2070-il1,000,000994.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2070-il1,000,000586.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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