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Wind-Tunnel Investigation of Control-Surface Characteristics XVI : Pressure Distribution over an NACA 0009 Airfoil with 0.30-Airfoil-Chord Beveled-Trailing-Edge Flaps

Marjorie E Bulloch

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Abstract

Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. From Summary: flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces.

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What this paper is about

Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. From Summary: flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces.

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Available abstract

Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. From Summary: flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces.

Key concepts: Airfoil, Chord (peer-to-peer), NACA airfoil, Trailing edge, Bevel, Wind tunnel, Leading edge, Aerodynamics

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Wind-Tunnel Investigation of Control-Surface Characteristics XVI : Pressure Distribution over an NACA 0009 Airfoil with 0.30-Airfoil-Chord Beveled-Trailing-Edge Flaps — Research Paper | ScholarLens