Date of Award

Spring 1994

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Engineering Mechanics

Committee Director

Osama A. Kandil

Committee Member

Colin P. Britcher

Committee Member

Woodrow Whitlow, Jr.

Committee Member

Samuel R. Bland

Call Number for Print

Special Collections; LD4331.E57M37

Abstract

A simulation of tail buffet is presented for a delta wing-vertical tail configuration. Flow conditions are chosen such that the wing primary-vortex cores experience vortex breakdown and the resulting turbulent wake flow impinges on the vertical tail. The dimensions and material properties of the vertical tail are chosen such that the deflections are large enough to insure interaction with the flow, and the natural frequencies are high enough to facilitate a practical computational solution. This multidisciplinary problem is solved sequentially for the fiuid flow, the elastic deformations and the grid displacements. The fluid flow is simulated by time accurately solving the laminar, unsteady, compressible, full Navier-Stokes equations using an implicit, upwind, flux-vector splitting finite volume scheme. The elastic vibrations of the tail are modeled by coupled bending and torsion beam equations. These equations are solved accurately in time using the Galerkin method and a five-stage Runge-Kutta-Verner scheme. The grid for the fluid dynamics calculations is continuously deformed using interpolation functions to smoothly disperse the displacements throughout the computational domain. The tail buffet problem is solved for three aeroelastic response cases: bending, coupled bending-torsion, and uncoupled bending-torsion. The results show that the vortex breakdown location is unsteady, asymmetric and sensitive to the vibrations of the tail. The addition of torsional vibration modes is seen to have a substantial effect on the tail response in comparison to the bending only case. The results also show that the deflections and loads of the coupled bending-torsion case are substantially lower than those of the uncoupled response case.

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DOI

10.25777/7etn-1m62

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