NACA 0024 (naca0024-il)
NACA 0024 - NACA 0024 airfoil
| Details | Dat file | Parser | |
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(naca0024-il) NACA 0024 NACA 0024 airfoil Max thickness 24% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 0024 1.0000 0.00252 0.9500 0.01613 0.9000 0.02896 0.8000 0.05247 0.7000 0.07328 0.6000 0.09127 0.5000 0.10588 0.4000 0.11607 0.3000 0.12004 0.2500 0.11883 0.2000 0.11475 0.1500 0.10691 0.1000 0.09365 0.0750 0.08400 0.0500 0.07109 0.0250 0.05229 0.0125 0.03788 0.0000 0.00000 0.0125 -0.03788 0.0250 -0.05229 0.0500 -0.07109 0.0750 -0.08400 0.1000 -0.09365 0.1500 -0.10691 0.2000 -0.11475 0.2500 -0.11883 0.3000 -0.12004 0.4000 -0.11607 0.5000 -0.10588 0.6000 -0.09127 0.7000 -0.07328 0.8000 -0.05247 0.9000 -0.02896 0.9500 -0.01613 1.0000 -0.00252 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 0024 (naca0024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0024-il | 50,000 | 9 | 15.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 50,000 | 5 | 21.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 9 | 34.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 5 | 30.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 9 | 43 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 5 | 37 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 9 | 52.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 5 | 50.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 9 | 68.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 5 | 64.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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