NACA 11-H-09 AIRFOIL (n11h9-il)
NACA 11-H-09 AIRFOIL - NACA 11-H-9 rotorcraft airfoil
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(n11h9-il) NACA 11-H-09 AIRFOIL NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord. Max camber 4.5% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 11-H-09 AIRFOIL
19. 19.
0.0000000 0.0000000
0.0034000 0.0127000
0.0078000 0.0174000
0.0200000 0.0266000
0.0447000 0.0400000
0.0699000 0.0502000
0.0952000 0.0585000
0.1461000 0.0711000
0.1973000 0.0799000
0.2484000 0.0857000
0.2996000 0.0889000
0.4022000 0.0883000
0.5039000 0.0772000
0.6039000 0.0597000
0.7029000 0.0391000
0.8015000 0.0184000
0.9001999 0.0017000
0.9499000 0.0027000
1.0000000 0.0000000
0.0000000 0.0000000
0.0116000 -.0031000
0.0171000 -.0031000
0.0300000 -.0024000
0.0552000 -.0009000
0.0801000 -.0004000
0.1048000 0.0013000
0.1538000 0.0025000
0.2027000 0.0028000
0.2516000 0.0023000
0.3004000 0.0014000
0.3978000 -.0014000
0.4961000 -.0051000
0.5961000 -.0089000
0.6970000 -.0117000
0.7985000 -.0127000
0.8998001 -.0105000
0.9501000 -.0071000
1.0000000 0.0000000
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Polars for NACA 11-H-09 AIRFOIL (n11h9-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n11h9-il | 50,000 | 9 | 24.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 50,000 | 5 | 24.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 100,000 | 9 | 52.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 100,000 | 5 | 53.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 200,000 | 9 | 79.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 200,000 | 5 | 79.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 500,000 | 9 | 114.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 500,000 | 5 | 109.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 1,000,000 | 9 | 138.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 1,000,000 | 5 | 125 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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