CLARK X AIRFOIL (clarkx-il)
CLARK X AIRFOIL - CLARK X airfoil
| Details | Dat file | Parser | |
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(clarkx-il) CLARK X AIRFOIL CLARK X airfoil Max thickness 11.7% at 30% chord. Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
CLARK X AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0186000
0.0250000 0.0276000
0.0500000 0.0416000
0.0750000 0.0522000
0.1000000 0.0608000
0.1500000 0.0728000
0.2000000 0.0808000
0.3000000 0.0890000
0.4000000 0.0900000
0.5000000 0.0852000
0.6000000 0.0755000
0.7000000 0.0615000
0.8000000 0.0442000
0.9000000 0.0240000
0.9500000 0.0129000
1.0000000 0.0012000
0.0000000 0.0000000
0.0125000 -.0163000
0.0250000 -.0220000
0.0500000 -.0272000
0.0750000 -.0296000
0.1000000 -.0310000
0.1500000 -.0318000
0.2000000 -.0317000
0.3000000 -.0280000
0.4000000 -.0240000
0.5000000 -.0200000
0.6000000 -.0160000
0.7000000 -.0120000
0.8000000 -.0080000
0.9000000 -.0040000
0.9500000 -.0020000
1.0000000 0.0000000
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Polars for CLARK X AIRFOIL (clarkx-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkx-il | 50,000 | 9 | 32.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkx-il | 50,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkx-il | 100,000 | 9 | 54.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkx-il | 100,000 | 5 | 55.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkx-il | 200,000 | 9 | 76.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkx-il | 200,000 | 5 | 72.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkx-il | 500,000 | 9 | 103.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkx-il | 500,000 | 5 | 92.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkx-il | 1,000,000 | 9 | 122.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkx-il | 1,000,000 | 5 | 107.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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