Accession Number:

ADA443140

Title:

Three-Dimensional Unsteady Laminar Shock-Wave/Boundary Layer Interaction

Descriptive Note:

Conference paper

Corporate Author:

LABORATORY OF DIGITAL SIMULATION IN MECHANICS OF FLUIDS (SINUMEF) PARIS (FRANCE) DIRECTION DE LA RECHERCHE (ENSAM)

Personal Author(s):

Report Date:

2004-10-01

Pagination or Media Count:

11.0

Abstract:

The objective of this work is to demonstrate that the low frequency behavior experimentally observed in shock waveboundary layer interaction SWBLI can be linked to the intrinsic dynamics of the detached zone induced by the interaction, independent of the boundary layer turbulent characteristics. To this end, the authors decided to study the evolution of the interaction between an incident shock wave and a laminar boundary layer developing over a flat plate when the incident shock angle is gradually increased, while keeping constant the free stream Mach number and the Reynolds number. The interaction of an oblique shock wave with a laminar boundary layer over an adiabatic flat-plate is computed. The test-case considered was experimentally and numerically studied by Degrez et al. The free stream Mach number is 2.15 for the numerical simulation. The Reynolds number based on the distance Xsub sh between the plate leading edge and the shock impingement point is 10exp 5. The shock angle with respect to the horizontal is initially equal to theta 30.8 degrees, which corresponds to a shock generator angle of 3.75 degrees. This data set takes into account confinement, 3D effects, and measurement approximations it is not strictly the same as the experiment free stream conditions. The evolution of the SWBLI when the incident shock angle increases is a very complex problem. Indeed, for a particular value of the angle theta, the flow becomes transitional in the interaction zone. This transitional state will probably modify substantially the topology and the temporal dynamics of the interaction zone. In this paper, 3D computations are done without taking into account the transitional character of the flow. A numerical solution of the shock-wavelaminar boundary-layer interaction is obtained by solving the 3D unsteady compressible Navier-Stokes equations written in conservative form.

Subject Categories:

  • Numerical Mathematics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE