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

EH 1.0/9.0 (eh1090-il)

EH 1.0/9.0 - John Yost EH 1.0/9.0 for tailless R/C aircraft


Airfoil eh1090-il
Details Dat file Parser  
(eh1090-il) EH 1.0/9.0
John Yost EH 1.0/9.0 for tailless R/C aircraft
Max thickness 9% at 28.7% chord.
Max camber 1% at 25.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
EH 1.0/9.0
1.000000     0.000000
0.996057     0.000150
0.991144     0.000412
0.984292     0.000870
0.975528     0.001533
0.964888     0.002385
0.952414     0.003411
0.938153     0.004606
0.922164     0.005974
0.904508     0.007522
0.885257     0.009252
0.864484     0.011162
0.842274     0.013243
0.818712     0.015482
0.793893     0.017866
0.767913     0.020379
0.740877     0.023002
0.712890     0.025715
0.684062     0.028493
0.654508     0.031310
0.624345     0.034136
0.593691     0.036938
0.562667     0.039680
0.531395     0.042324
0.500000     0.044828
0.468605     0.047149
0.437333     0.049242
0.406309     0.051063
0.375655     0.052568
0.345492     0.053716
0.315938     0.054469
0.287110     0.054791
0.259123     0.054655
0.232087     0.054041
0.206107     0.052936
0.181208     0.051338
0.157726     0.049255
0.135516     0.046708
0.114743     0.043724
0.095492     0.040341
0.077836     0.036606
0.061547     0.032578
0.047586     0.028317
0.035112     0.023893
0.024472     0.019387
0.015708     0.014910
0.008856     0.010617
0.003943     0.006667
0.000987     0.003149
0.000000     0.000000
0.000987    -0.002963
0.003943    -0.005931
0.008856    -0.008987
0.015708    -0.012080
0.024472    -0.015094
0.035112    -0.017932
0.047586    -0.020548
0.061547    -0.022927
0.077836    -0.025071
0.095492    -0.026985
0.114743    -0.028678
0.135516    -0.030159
0.157726    -0.031439
0.181288    -0.032530
0.206107    -0.033439
0.232087    -0.034171
0.259123    -0.034730
0.287110    -0.035120
0.315938    -0.035340
0.345492    -0.035392
0.375655    -0.035271
0.406309    -0.034974
0.437333    -0.034498
0.469605    -0.033839
0.500000    -0.032996
0.531395    -0.031970
0.562667    -0.030766
0.593631    -0.029394
0.624345    -0.027865
0.654508    -0.026196
0.684062    -0.024406
0.712890    -0.022513
0.740877    -0.020561
0.767913    -0.018562
0.793893    -0.016552
0.818712    -0.014561
0.842274    -0.012621
0.864484    -0.010759
0.885257    -0.009003
0.904508    -0.007377
0.922164    -0.005896
0.938153    -0.004568
0.952414    -0.003394
0.964888    -0.002379
0.975528    -0.001532
0.984292    -0.000870
0.991144    -0.000412
0.996057    -0.000150
1.000000     0.000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

PW51PreviewDetails
EH 1.5/9.0PreviewDetails
PW75PreviewDetails
SIKORSKY SC1095 AIRFOILPreviewDetails
BOEING VERTOL V(1.95)3009-1.25PreviewDetails
E221 (9.39%)PreviewDetails
PW98-modPreviewDetails
ONERA OA209 AIRFOILPreviewDetails
GIII BL332 AIRFOILPreviewDetails
PW106PreviewDetails

Polars for EH 1.0/9.0 (eh1090-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   eh1090-il50,000929.2 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   eh1090-il50,000531.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   eh1090-il100,000943.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh1090-il100,000543 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   eh1090-il200,000956.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   eh1090-il200,000554.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   eh1090-il500,000974.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   eh1090-il500,000568.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   eh1090-il1,000,000984.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh1090-il1,000,000573.4 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit