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Vortex Effects for Canard-wing Configurations at High Angles of Attack in Subsonic Flow (1978)

Medan, R. T. ; Desilva, B. M. E.

In: CASI

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Publication Date: 2019-06-27

Description: A fully three-dimensional subsonic panel method that can handle arbitrary shed vortex wakes is used to compute the nonlinear forces and moments on simple canard-wing configurations. The lifting surfaces and wakes are represented by doublet panels. The Mangler-Smith theory is used to provide an initial estimate for the vortex sheet shed from the leading edge. The trailing-edge wake and the leading-edge wake downstream of the trailing edge are assumed to be straight and leave the trailing edge at an angle of alpha/2. Results indicate good agreement with experimental data up to 40 degs angle of attack.

Keywords: AERODYNAMICS

Type: NASA-TM-78543 , A-7677

Format: application/pdf

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