EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
EPPLER EC 86(-3)-914 AIRFOIL - Eppler EC 86(-3)-914 airfoil
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(ec863914-il) EPPLER EC 86(-3)-914 AIRFOIL Eppler EC 86(-3)-914 airfoil Max thickness 14.3% at 35.5% chord. Max camber 4.4% at 71.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER EC 86(-3)-914 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0017000 0.0106000
0.0109000 0.0230000
0.0484000 0.0505000
0.1089000 0.0757000
0.1478000 0.0851000
0.1929000 0.0928000
0.2972000 0.1032000
0.3547000 0.1059000
0.4757000 0.1061000
0.5977000 0.0994000
0.7123001 0.0863000
0.8134000 0.0673000
0.9303000 0.0289000
0.9803000 0.0079000
1.0000000 0.0000000
0.0000000 0.0000000
0.0009000 -.0006000
0.0102000 -.0078000
0.0282000 -.0168000
0.0530000 -.0254000
0.0845000 -.0329000
0.1216000 -.0383000
0.2155000 -.0409000
0.3314000 -.0379000
0.4594000 -.0309000
0.5885000 -.0192000
0.7166001 0.0023000
0.8421000 0.0186000
0.9451000 0.0152000
0.9772000 0.0075000
1.0000000 0.0000000
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Polars for EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ec863914-il | 50,000 | 9 | 34.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 50,000 | 5 | 32.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 100,000 | 9 | 50.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 100,000 | 5 | 44.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 200,000 | 9 | 62.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 200,000 | 5 | 63 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 500,000 | 9 | 103.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 500,000 | 5 | 98.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 1,000,000 | 9 | 150.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 1,000,000 | 5 | 101 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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