Unsteady Navier-Stokes computations past oscillating delta wing at high incidence

The unsteady, compressible, thin-layer, Navier-Stokes equations, written in the moving frame of reference for the flow relative motion, are solved for the unsteady supersonic flow around-edged delta wing. For supersonic flow, a local conical flow solution has been obtained from the three-dimensional...

Full description

Saved in:
Bibliographic Details
Published in:AIAA journal 1990-09, Vol.28 (9), p.1565-1572
Main Authors: Kandil, Osama A, Chuang, H. Andrew
Format: Article
Language:English
Subjects:
Aerodynamics
Applied fluid mechanics
compressible fluids
delta wings
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
supersonic flow
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:The unsteady, compressible, thin-layer, Navier-Stokes equations, written in the moving frame of reference for the flow relative motion, are solved for the unsteady supersonic flow around-edged delta wing. For supersonic flow, a local conical flow solution has been obtained from the three-dimensional equations. Pseudo time stepping is used for the steady flow problem; while time-accurate stepping is used for the unsteady flow problem. The computational scheme is an implicit, approximately factored, finite-volume scheme, which uses implicit and explicit dissipation terms. The scheme is then applied to a delta wing undergoing rolling oscillation at a reduced frequency of 1.337 with 15-deg maximum amplitude about a mean angle of attack of 10 deg for a Mach number of 2 and a Reynolds number of 0.5 x 10 super(6).
ISSN:0001-1452
1533-385X
DOI:10.2514/3.25254