Leading Edge of a Shock-Induced Boundary Layer

Model Uncertainties in a Sharp Leading-Edge Hypersonic Boundary Layer

The effects of uncertainties in the gas-surface interaction and intermolecular interaction models on the hypersonic boundary layer development are investigated using the non-intrusive generalized polynomial chaos method. In particular, uncertainties in the surface shear stress, normal stress, heat flux, flowfield temperature and density resulting from uncertain viscosity exponent, surface tempe...

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...

Effect of a Sinusoidal Leading Edge Pattern on Flat Plate Boundary Layer Flow

Aerofoils with a sinusoidal leading edge pattern have been the subject of the study during the recent decade due to its considerable effect on the aerodynamics performance. The leading edge variation results in the formation of streamwise counterrotating vortices which affect the boundary layer development on aerofoils. To understand the influence of the leading edge variation to the boundary l...

Edge states in a boundary layer

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

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...