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Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method

John A. Zalovcik, R. H. Sawyer

Open publisher page 1 citations

Abstract

Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.

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What this paper is about

Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.

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Available abstract

Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.

Key concepts: Transonic, Airplane, Wing, Longitudinal static stability, Angle of attack, Elevator, Trim, Swept wing

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Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method — Research Paper | ScholarLens