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1959•Unpublished venueRequires access

Effects of components and various modifications on the drag and the static stability and control characteristics of a 42 deg swept-wing fighter-airplane model at Mach numbers of 1.60 to 2.50

James D. Church

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Abstract

Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.

About this research paper

What this paper is about

Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.

Why it matters

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Key contribution

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Method / approach

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Main findings

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Available abstract

Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.

Key concepts: Airplane, Wing, Longitudinal static stability, Drag, Aerospace engineering, Mach number, Lift-induced drag, Wing configuration

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Effects of components and various modifications on the drag and the static stability and control characteristics of a 42 deg swept-wing fighter-airplane model at Mach numbers of 1.60 to 2.50 — Research Paper | ScholarLens