NACA 6-H-10 AIRFOIL (n6h10-il)
NACA 6-H-10 AIRFOIL - NACA 6-H-10 rotorcraft airfoil
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(n6h10-il) NACA 6-H-10 AIRFOIL NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord. Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 6-H-10 AIRFOIL
18. 18.
0.0000000 -.0011400
0.0125000 0.0191600
0.0250000 0.0275900
0.0500000 0.0386000
0.0750000 0.0476000
0.1000000 0.0560000
0.1500000 0.0693800
0.2000000 0.0794000
0.2500000 0.0876900
0.3000000 0.0920000
0.4000000 0.0951700
0.5000000 0.0853700
0.6000000 0.0653000
0.7000000 0.0411400
0.8000000 0.0197100
0.9000000 0.0057100
0.9500000 0.0011000
1.0000000 0.0000000
0.0000000 -.0011400
0.0125000 -.0039200
0.0250000 -.0044900
0.0500000 -.0046000
0.0750000 -.0042800
0.1000000 -.0033500
0.1500000 -.0019800
0.2000000 -.0016100
0.2500000 -.0019900
0.3000000 -.0030900
0.4000000 -.0050000
0.5000000 -.0097900
0.6000000 -.0168000
0.7000000 -.0228300
0.8000000 -.0235600
0.9000000 -.0130000
0.9500000 -.0068000
1.0000000 0.0000000
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Polars for NACA 6-H-10 AIRFOIL (n6h10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6h10-il | 50,000 | 9 | 23.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 50,000 | 5 | 17.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 100,000 | 9 | 48.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 100,000 | 5 | 44.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 200,000 | 9 | 71.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 200,000 | 5 | 68.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 500,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 500,000 | 5 | 87.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 1,000,000 | 9 | 107.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 1,000,000 | 5 | 99.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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