NACA 16-021 (naca16021-il)
NACA 16-021 - NACA 16-021 airfoil
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(naca16021-il) NACA 16-021 NACA 16-021 airfoil Max thickness 21% at 50% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 16-021 1.0000 0.00210 0.9500 0.02476 0.9000 0.04405 0.8000 0.07348 0.7000 0.09221 0.6000 0.10211 0.5000 0.10500 0.4000 0.10246 0.3000 0.09480 0.2000 0.08162 0.1500 0.07236 0.1000 0.06050 0.0750 0.05306 0.0500 0.04391 0.0250 0.03159 0.0125 0.02261 0.0000 0.00000 0.0125 -0.02261 0.0250 -0.03159 0.0500 -0.04391 0.0750 -0.05306 0.1000 -0.06050 0.1500 -0.07236 0.2000 -0.08162 0.3000 -0.09480 0.4000 -0.10246 0.5000 -0.10500 0.6000 -0.10211 0.7000 -0.09221 0.8000 -0.07348 0.9000 -0.04405 0.9500 -0.02476 1.0000 -0.00210 |
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Polars for NACA 16-021 (naca16021-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16021-il | 50,000 | 9 | 21.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 50,000 | 5 | 17.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 100,000 | 9 | 28.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 100,000 | 5 | 20.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 200,000 | 9 | 33.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 200,000 | 5 | 26.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 500,000 | 9 | 39.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 500,000 | 5 | 28.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 1,000,000 | 9 | 42 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 1,000,000 | 5 | 31.6 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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