A MODULAR PARTICLE-CONTINUUM NUMERICAL ALGORITHM FORHYPERSONIC NON-EQUILIBRIUM FLOWS byThomas Edward Schwartzentruber Chairperson: Iain D. Boyd Hypersonic vehicles traveling at high altitudes experience conditions ranging fromrarefied to continuum flow. Even within a mostly continuum flow, there may belocal regions of rarefied (or non-equilibrium) flow generated by sharp leading...

Matsumura, Shin. Master of Science in Aeronautics and Astronautics, Purdue University, December, 2003. Streamwise Vortex Instability and Hypersonic BoundaryLayer Transition on the Hyper-2000. Major Professor: Steven P. Schneider. Despite the closely coupled multidisciplinary design of hypersonic airbreathing vehicles, the boundary layer transition mechanisms that are important on the forebody a...

The receptivity of a Mach 5.92 flat plate boundary layer to periodic two-dimensional wall perturbations is studied by numerical simulations and linear stability theory LST . Free stream flow conditions are the same as the leading edge receptivity experiment of Maslov et al., J. Fluid Mech. 426, 73 2001 . Steady base flow is simulated by solving compressible Navier–Stokes equations with a combin...

Hypersonic boundary-layer transition can be affected significantly by surface roughness. Many important mechanisms which involve transition induced by arbitrary roughness are not well understood. Direct numerical simulation is broadly applied for investigating the roughness induced instability and transition in recent decade. But due to the complex computational geometry with embedded 3-D rough...