Numerical-simulation of boundary-layer-transition at Mach 2


Sandham, N.D. and Adams, N.A. (1993) Numerical-simulation of boundary-layer-transition at Mach 2. Applied Scientific Research, 51, (1-2), 371-375. (doi:10.1007/BF01082563).

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Original Publication URL: http://dx.doi.org/10.1007/BF01082563

Description/Abstract

The linear and early nonlinear stages of boundary-layer transition at free-stream Mach numberM ∞==2.0 are investigated by direct numerical simulation of the compressible Navier-Stokes equations. Results from simulations with a large computational box and small-amplitude random initial conditions are compared with linear stability theory. The growth rates of oblique waves are reproduced correctly. Two-dimensional waves show a growth that is modulated in time, indicating the presence of an extra unstable mode which moves supersonically relative to the free stream. Further simulations are conducted to investigate the nonlinear development of two- and three-dimensional disturbances The transition due to oblique disturbance waves is the most likely cause of transition at this Mach number, and is found to lead to the development of strong streamwise vortices

Item Type: Article
ISSNs: 0003-6994 (print)
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Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions: University Structure - Pre August 2011 > School of Engineering Sciences
ePrint ID: 72045
Date Deposited: 18 Jan 2010
Last Modified: 27 Mar 2014 18:51
URI: http://eprints.soton.ac.uk/id/eprint/72045

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