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Investigation of drag and static longitudinal and lateral stability characteristics of a model of a 40.4 degree swept-wing airplane at Mach numbers of 1.56 and 2.06

Melvin M Carmel, Kenneth L Turner

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Abstract

Wind tunnel test to determine swept wing fighter aircraft drag, and logitudinal and lateral stablity at supersonic speeds.

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What this paper is about

Wind tunnel test to determine swept wing fighter aircraft drag, and logitudinal and lateral stablity at supersonic speeds.

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Available abstract

Wind tunnel test to determine swept wing fighter aircraft drag, and logitudinal and lateral stablity at supersonic speeds.

Key concepts: Airplane, Wing, Longitudinal static stability, Degree (music), Mach number, Drag, Lift-induced drag, Wing configuration

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Investigation of drag and static longitudinal and lateral stability characteristics of a model of a 40.4 degree swept-wing airplane at Mach numbers of 1.56 and 2.06 — Research Paper | ScholarLens