1951•NASA STI Repository (National Aeronautics and Space Administration)Requires access

The Effect on Zero-lift Drag of an Indented Fuselage or a Thickened Wing-root Modification to a 45 Degrees Sweptback Wing-body Configuration as Determined by Flight Tests at Transonic Speeds

W. PEPPER

Abstract

Report presenting a study of rocket-powered models at transonic speeds to determine the effect on the zero-lift drag coefficient of an indented fuselage modification and a thickened wing-root modification of a swept-wing airplane configuration. Results regarding the variation of drag coefficient with Mach number, effect of wing root thickening, and wing-plus-interference drag coefficients for the tested models 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: Wing, Fuselage, Transonic, Lift-to-drag ratio, Drag, Airplane, Angle of attack, Lift coefficient