1956•NASA STI Repository (National Aeronautics and Space Administration)Requires access

Static Lateral Stability and Control Characteristics of a Model of a 45 Degree Swept-wing Fighter Airplane with Various Vertical Tails at Mach Numbers of 1.41, 1.61, and 2.01

M Leroy Srearman, Ross B Robinson

Abstract

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of a model of a 45 degree swept-wing fighter airplane. Results regarding the static stability characteristics and lateral and directional control are provided.

About this research paper

What this paper is about

Why it matters

A significance statement is not available in the OpenAlex record.

Key contribution

A contribution statement is not available in the OpenAlex record.

Method / approach

Method details are not available in the OpenAlex metadata.

Main findings

Findings are not separately available in the OpenAlex metadata.

Limitations

Limitations are not available in the OpenAlex metadata.

Applications

Application details are not available in the OpenAlex metadata.

Available abstract

Key concepts: Airplane, Mach number, Supersonic speed, Wing, Longitudinal static stability, Aerospace engineering, Angle of attack, Degree (music)