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

EH 2.5/10 (eh2510-il)

EH 2.5/10 - John Yost EH 2.5/10 for tailless R/C aircraft


Airfoil eh2510-il
Details Dat file Parser  
(eh2510-il) EH 2.5/10
John Yost EH 2.5/10 for tailless R/C aircraft
Max thickness 10% at 30% chord.
Max camber 2.5% at 25% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
EH 2.5/10
  1.00000  0.00000
  0.99000  0.00084
  0.98000  0.00169
  0.97000  0.00256
  0.95000  0.00432
  0.92500  0.00663
  0.90000  0.00905
  0.87500  0.01161
  0.85000  0.01430
  0.82500  0.01712
  0.80000  0.02005
  0.77500  0.02306
  0.75000  0.02613
  0.72500  0.02926
  0.70000  0.03245
  0.67500  0.03568
  0.65000  0.03894
  0.60000  0.04548
  0.55000  0.05190
  0.50000  0.05804
  0.45000  0.06365
  0.40000  0.06847
  0.35000  0.07216
  0.30000  0.07430
  0.27500  0.07465
  0.25000  0.07442
  0.22500  0.07353
  0.20000  0.07189
  0.17500  0.06940
  0.15000  0.06592
  0.12500  0.06130
  0.10000  0.05534
  0.07500  0.04773
  0.05000  0.03795
  0.03500  0.03064
  0.02500  0.02486
  0.02000  0.02158
  0.01500  0.01797
  0.01250  0.01602
  0.01000  0.01396
  0.00750  0.01171
  0.00500  0.00916
  0.00400  0.00901
  0.00300  0.00676
  0.00250  0.00609
  0.00200  0.00538
  0.00150  0.00461
  0.00100  0.00373
  0.00050  0.00263
  0.00000  0.00032
  0.00050 -0.00187
  0.00100 -0.00288
  0.00150 -0.00365
  0.00200 -0.00430
  0.00250 -0.00487
  0.00300 -0.00538
  0.00400 -0.00624
  0.00500 -0.00696
  0.00750 -0.00835
  0.01000 -0.00939
  0.01250 -0.01030
  0.01500 -0.01115
  0.02000 -0.01265
  0.02500 -0.01391
  0.03500 -0.01580
  0.05000 -0.01769
  0.07500 -0.01969
  0.10000 -0.02089
  0.12500 -0.02173
  0.15000 -0.02241
  0.17500 -0.02300
  0.20000 -0.02354
  0.22500 -0.02405
  0.25000 -0.02456
  0.27500 -0.02510
  0.30000 -0.02564
  0.35000 -0.02670
  0.40000 -0.02760
  0.45000 -0.02823
  0.50000 -0.02846
  0.55000 -0.02817
  0.60000 -0.02727
  0.65000 -0.02571
  0.67500 -0.02468
  0.70000 -0.02348
  0.72000 -0.02212
  0.75000 -0.02058
  0.77500 -0.01888
  0.80000 -0.01702
  0.82500 -0.01503
  0.85000 -0.01297
  0.87500 -0.01087
  0.90000 -0.00874
  0.92500 -0.00658
  0.95000 -0.00440
  0.97000 -0.00264
  0.98000 -0.00176
  0.99000 -0.00088
  1.00000  0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EH 2.0/10PreviewDetails
M6 (85%)PreviewDetails
SIKORSKY SC1094 R8 AIRFOILPreviewDetails
USA 51 AIRFOILPreviewDetails
BELL/WORTMANN FX 69-H-098 AIRFOILPreviewDetails
SIKORSKY SC1094R8 AIRFOILPreviewDetails
S5010PreviewDetails
BOEING-VERTOL VR-12 AIRFOILPreviewDetails
BOEING-VERTOL VR-13 AIRFOILPreviewDetails
S4094 (root airfoil designed for andPreviewDetails

Polars for EH 2.5/10 (eh2510-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   eh2510-il50,000926.5 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2510-il50,000530.9 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2510-il100,000947 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2510-il100,000548 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2510-il200,000965.2 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2510-il200,000556.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2510-il500,000991.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2510-il500,000562.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   eh2510-il1,000,0009111.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   eh2510-il1,000,000571.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit