A Modified Flux Vector Splitting Scheme for Flow Analysis in Shock Wave Laminar Boundary Layer Interactions

Authors

  • A. Shadaram
  • H. Khaleghi and M.S. Sadeghipour
Abstract:

The present work introduces a modified scheme for the solution of compressible 2-D full Navier-Stokes equations, using Flux Vector Splitting method. As a result of this modification, numerical diffusion is reduced. The computer code which is developed based on this algorithm can be used easily and accurately to analyze complex flow fields with discontinuity in properties, in cases such as shock wave boundary layer interactions. This scheme combines advantages of both Advective Upstream Splitting (AUSM) and Low Diffusion Flux Vector Splitting (LDFVS) Methods. To increase accuracy and monotonicity, the conservative variables are extrapolated at the cell interfaces by using the MUSCL approach with limiter. This algorithm has been used to solve four sample problems. It has been shown that the numerical diffusion has been reduced and the results are in good agreement with published numerical and/or experimental data. Keywords: Compressible Navier Stokes Equations, Flux Vector splitting, Advective upwind, Numerical diffusion

Upgrade to premium to download articles

Sign up to access the full text

Already have an account?login

similar resources

Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow

Numerical results are presented for the shock-boundary layer interactions in a hypersonic flow over a sharp leading edge compression corner. In this study, a second- order Godunov type scheme based on solving a Generalized Riemann Problem (GRP) at each cell interface is used to solve thin shear layer approximation of laminar Navier-Stokes (N-S) equations. The calculated flow-field shows general...

full text

Flow Visualization for Shock Wave / Boundary Layer Interactions on the Front Edge of Flat Plate

In engineering practice, when the flight Mach number is beyond the design Mach number, or the actual flight attack exceeds rated value, the waves generated by forebody would interact with lip boundary layer, which may result in inlet unstart. In figure 1, a sizable wave pattern occurs at the lip leading edge, which includes various basic physical appearances such as viscous flow, separation, an...

full text

Experimental Investigation of Shock-Wave/Boundary- Layer Interactions Over an Artificially Heated Model in Hypersonic Flow

Experimental tests have been carried out to analyze the effect of wall-to-total temperature ratio on the characteristics of a fully laminar shock-wave/boundary-layer interaction in a Mach 6 high enthalpy flow. Test cases were run in a new high-enthalpy arc-heated wind tunnel developed at Centrospazio in the framework of the ESA/FESTIP program. In order to heat-up the model surface a high temper...

full text

Laminar Boundary Layer Flow of Sisko Fluid

full text

Micro-Ramp Flow Control of Normal Shock/Boundary Layer Interactions

Boundary layer bleed has conventionally been used to control separation due to shock wave / boundary layer interactions (SBLIs) within supersonic engine inlets. However, bleed systems result in a loss of captured mass flow, incurring higher drag and ultimately lower propulsion system efficiency. Micro-ramp sub-boundary layer vortex generators (SBVGs) arranged in a spanwise array have been propo...

full text

My Resources

Save resource for easier access later

Save to my library Already added to my library

{@ msg_add @}


Journal title

volume 20  issue 2

pages  167- 180

publication date 2001-04

{@ msg @}

By following a journal you will be notified via email when a new issue of this journal is published.

Keywords

Hosted on Doprax cloud platform doprax.com

copyright © 2015-2023