EPPLER 625 AIRFOIL (e625-il)
EPPLER 625 AIRFOIL - Eppler E625 airfoil
| Details | Dat file | Parser | |
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(e625-il) EPPLER 625 AIRFOIL Eppler E625 airfoil Max thickness 13% at 30% chord. Max camber 2.9% at 22.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 625 AIRFOIL
50. 50.
0.0000000 0.0002400
0.0005000 0.0041700
0.0010000 0.0058800
0.0015000 0.0072900
0.0020000 0.0085500
0.0025000 0.0097300
0.0030000 0.0108400
0.0040000 0.0129000
0.0050000 0.0147700
0.0075000 0.0188600
0.0100000 0.0223500
0.0125000 0.0254300
0.0150000 0.0282300
0.0200000 0.0332200
0.0250000 0.0376300
0.0350000 0.0452100
0.0500000 0.0544200
0.0750000 0.0660300
0.1000000 0.0745400
0.1250000 0.0808800
0.1500000 0.0855800
0.1750000 0.0889300
0.2000000 0.0911800
0.2250000 0.0925100
0.2500000 0.0930900
0.2750000 0.0930600
0.3000000 0.0924800
0.3500000 0.0899600
0.4000000 0.0859200
0.4500000 0.0806700
0.5000000 0.0744500
0.5500000 0.0674900
0.6000000 0.0599600
0.6500000 0.0520300
0.6750000 0.0479900
0.7000000 0.0439100
0.7250000 0.0398200
0.7500000 0.0357400
0.7750000 0.0317000
0.8000000 0.0277100
0.8250000 0.0238000
0.8500000 0.0199900
0.8750000 0.0163300
0.9000000 0.0128000
0.9250000 0.0094300
0.9500000 0.0061900
0.9700000 0.0036800
0.9800000 0.0024400
0.9900000 0.0012100
1.0000000 0.0000000
0.0000000 0.0002400
0.0005000 -.0033100
0.0010000 -.0046800
0.0015000 -.0057200
0.0020000 -.0065800
0.0025000 -.0073200
0.0030000 -.0079600
0.0040000 -.0090200
0.0050000 -.0098800
0.0075000 -.0114900
0.0100000 -.0126800
0.0125000 -.0136700
0.0150000 -.0145700
0.0200000 -.0162100
0.0250000 -.0176600
0.0350000 -.0200600
0.0500000 -.0227400
0.0750000 -.0258600
0.1000000 -.0280600
0.1250000 -.0297600
0.1500000 -.0311600
0.1750000 -.0323700
0.2000000 -.0334800
0.2250000 -.0345400
0.2500000 -.0355600
0.2750000 -.0365600
0.3000000 -.0375200
0.3500000 -.0393400
0.4000000 -.0408800
0.4500000 -.0420300
0.5000000 -.0427200
0.5500000 -.0428800
0.6000000 -.0424500
0.6500000 -.0413200
0.6750000 -.0404200
0.7000000 -.0392600
0.7250000 -.0378100
0.7500000 -.0360200
0.7750000 -.0338800
0.8000000 -.0313900
0.8250000 -.0285100
0.8500000 -.0252200
0.8750000 -.0215700
0.9000000 -.0176000
0.9250000 -.0134000
0.9500000 -.0090200
0.9700000 -.0054400
0.9800000 -.0036300
0.9900000 -.0018200
1.0000000 0.0000000
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Polars for EPPLER 625 AIRFOIL (e625-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e625-il | 50,000 | 9 | 18.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 50,000 | 5 | 28.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 100,000 | 9 | 39.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 100,000 | 5 | 44.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 200,000 | 9 | 58 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 200,000 | 5 | 60.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 500,000 | 9 | 82.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 500,000 | 5 | 76.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 1,000,000 | 9 | 96.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 1,000,000 | 5 | 93.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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