CLARK YS AIRFOIL (clarkys-il)
CLARK YS AIRFOIL - CLARK YS airfoil
| Details | Dat file | Parser | |
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(clarkys-il) CLARK YS AIRFOIL CLARK YS airfoil Max thickness 11.7% at 30% chord. Max camber 2.4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
CLARK YS AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0195000
0.0250000 0.0300000
0.0500000 0.0440000
0.0750000 0.0535000
0.1000000 0.0610000
0.1500000 0.0718000
0.2000000 0.0786000
0.3000000 0.0820000
0.4000000 0.0790000
0.5000000 0.0702000
0.6000000 0.0565000
0.7000000 0.0385000
0.8000000 0.0190000
0.9000000 0.0080000
0.9500000 0.0030000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0157000
0.0250000 -.0203000
0.0500000 -.0257000
0.0750000 -.0287000
0.1000000 -.0308000
0.1500000 -.0335000
0.2000000 -.0347000
0.3000000 -.0350000
0.4000000 -.0350000
0.5000000 -.0350000
0.6000000 -.0350000
0.7000000 -.0350000
0.8000000 -.0330000
0.9000000 -.0190000
0.9500000 -.0100000
1.0000000 0.0000000
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Polars for CLARK YS AIRFOIL (clarkys-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkys-il | 50,000 | 9 | 23.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 50,000 | 5 | 31.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 9 | 45.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 5 | 47 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 9 | 62.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 5 | 58.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 5 | 68.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 9 | 85.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 5 | 80.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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