NACA CYH (nacacyh-il)
NACA CYH - NACA CYH airfoil
| Details | Dat file | Parser | |
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(nacacyh-il) NACA CYH NACA CYH airfoil Max thickness 11.7% at 30% chord. Max camber 2.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA CYH 1.0000 0.0205 0.9500 0.0293 0.9000 0.0384 0.8000 0.0562 0.7000 0.0741 0.6000 0.0915 0.5000 0.1052 0.4000 0.1140 0.3000 0.1170 0.2000 0.1136 0.1500 0.1068 0.1000 0.0960 0.0750 0.0885 0.0500 0.0790 0.0250 0.0650 0.0125 0.0545 0.0000 0.0350 0.0125 0.0193 0.0250 0.0147 0.0500 0.0093 0.0750 0.0063 0.1000 0.0042 0.1500 0.0015 0.2000 0.0003 0.3000 0.0000 0.4000 0.0000 0.5000 0.0000 0.6000 0.0000 0.7000 0.0006 0.8000 0.0038 0.9000 0.0102 0.9500 0.0140 1.0000 0.0185 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA CYH (nacacyh-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacacyh-il | 50,000 | 9 | 25.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 5 | 33.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 9 | 47.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 5 | 49.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 9 | 65.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 5 | 64.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 9 | 90.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 9 | 110.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 5 | 101 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||