Shock oscillations on biconvex aerofoils

The mechanism of the origin of shock oscillations on an 18% thick biconvex aerofoil is investigated using a thin-layer Navier-Stokes code. The approach used in this study is to initiate shock oscillations on an aerofoil in transonic flow by moving the aerofoil from a regime of non-periodic flow to a...

Full description

Saved in:
Bibliographic Details
Published in:Aerospace science and technology 1999, Vol.3 (1), p.1-9
Main Authors: Raghunathan, S., Gillan, M.A., Cooper, R.K., Mitchell, R.D., Cole, J.S.
Format: Article
Language:English
Subjects:
Aerodynamics
Applied fluid mechanics
boundary layers
Compressible flows
shock and detonation phenomena
Computational methods in fluid dynamics
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
shock waves
Shock-wave interactions and shock effects
Shock-wave interactions and shockeffects
transonics
unsteady aerodynamics
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 mechanism of the origin of shock oscillations on an 18% thick biconvex aerofoil is investigated using a thin-layer Navier-Stokes code. The approach used in this study is to initiate shock oscillations on an aerofoil in transonic flow by moving the aerofoil from a regime of non-periodic flow to a regime where periodic flow does occur by withdrawal of a trailing-edge splitter plate. The results indicate that the shock induced separation plays a leading role in the origin of shock oscillations.
ISSN:1270-9638
1626-3219
DOI:10.1016/S1270-9638(99)80017-0