NACA 0010-65 (naca001065-il)
NACA 0010-65 - NACA 0010-65 airfoil
| Details | Dat file | Parser | |
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(naca001065-il) NACA 0010-65 NACA 0010-65 airfoil Max thickness 10% 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 0010-65 1.0000 0.00100 0.9500 0.01178 0.9000 0.02100 0.8000 0.03500 0.7000 0.04389 0.6000 0.04867 0.5000 0.05000 0.4000 0.04889 0.3000 0.04578 0.2000 0.04089 0.1500 0.03756 0.1000 0.03300 0.0750 0.02989 0.0500 0.02589 0.0250 0.01967 0.0125 0.01467 0.0000 0.00000 0.0125 -0.01467 0.0250 -0.01967 0.0500 -0.02589 0.0750 -0.02989 0.1000 -0.03300 0.1500 -0.03756 0.2000 -0.04089 0.3000 -0.04578 0.4000 -0.04889 0.5000 -0.05000 0.6000 -0.04867 0.7000 -0.04389 0.8000 -0.03500 0.9000 -0.02100 0.9500 -0.01178 1.0000 -0.00100 |
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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 0010-65 (naca001065-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca001065-il | 50,000 | 9 | 20.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 50,000 | 5 | 21.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 100,000 | 9 | 27.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 100,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 200,000 | 9 | 40.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 200,000 | 5 | 35.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 500,000 | 9 | 43.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 500,000 | 5 | 50.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 1,000,000 | 9 | 57.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 1,000,000 | 5 | 65.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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