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Naca Airfoils: NACA 0015

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NACA airfoil aerodynamic data — lift coefficient, drag coefficient, moment coefficient, and lift-to-drag ratio as functions of angle of attack for standard NACA airfoil profiles

Mechanical Engineeringairfoil id: NACA 001510 rowsPage 2 of 2
airfoil idangle of attack degCd (dimensionless)Cl (dimensionless)Cl Cd (dimensionless)Cm c4 (dimensionless)reynolds number (dimensionless)
NACA 001550.00680.5580.906,000,000
NACA 001560.00780.6684.606,000,000
NACA 001570.00920.7783.706,000,000
NACA 001580.01050.8782.906,000,000
NACA 0015100.0141.057506,000,000
NACA 0015120.021.26006,000,000
NACA 0015140.0311.3242.606,000,000
NACA 0015160.0481.3528.106,000,000
NACA 0015180.0781.215.406,000,000
NACA 0015200.1151.028.906,000,000

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