): Increases linearly with the angle of attack until reaching the stall point, typically between 12∘12 raised to the composed with power 15∘15 raised to the composed with power depending on the Reynolds number. Drag Coefficient ( CDcap C sub cap D
The comparison between experimental and numerical data for the NACA 0015 shows high correlation, though CFD models often slightly under-predict drag at high angles of attack. This profile remains a robust choice for applications requiring predictable symmetric performance.
Technical Report: Aerodynamic Characteristics of the NACA 0015 Airfoil 1. Abstract
): Increases linearly with the angle of attack until reaching the stall point, typically between 12∘12 raised to the composed with power 15∘15 raised to the composed with power depending on the Reynolds number. Drag Coefficient ( CDcap C sub cap D
The comparison between experimental and numerical data for the NACA 0015 shows high correlation, though CFD models often slightly under-predict drag at high angles of attack. This profile remains a robust choice for applications requiring predictable symmetric performance. Download 0015 txt
Technical Report: Aerodynamic Characteristics of the NACA 0015 Airfoil 1. Abstract ): Increases linearly with the angle of attack