High enthalpy Effects on two boundary layer disturbances in supersonic and hypersonic flow.
RM Wagnild - 2012 - conservancy.umn.edu
The fluid flow phenomenon of boundary layer transition is a complicated and difficult
process to model and predict. The importance of the state of the boundary layer with regard …
process to model and predict. The importance of the state of the boundary layer with regard …
Wake instabilities behind discrete roughness elements in high speed boundary layers
M Choudhari, A Norris, F Li, CL Chang… - 51st AIAA aerospace …, 2013 - arc.aiaa.org
Computations are performed to study the flow past an isolated, spanwise symmetric
roughness element in zero pressure gradient boundary layers at Mach 3.5 and 5.9, with an …
roughness element in zero pressure gradient boundary layers at Mach 3.5 and 5.9, with an …
Hypersonic boundary-layer flow with an obstacle in thermochemical equilibrium and nonequilibrium
The hypersonic flow around a tip of a rocket-mounted Hypersonic Boundary-Layer
Transition experiment has been simulated with direct numerical simulations. The numerical …
Transition experiment has been simulated with direct numerical simulations. The numerical …
Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element
Hypersonic boundary layer transition induced by an isolated cylindrical roughness element
is investigated using direct numerical simulation method based on a finite volume …
is investigated using direct numerical simulation method based on a finite volume …
Roughness-induced transition in high speed flows
Transition causes undesirable increase in drag and heating rates. Both discrete and
distributed roughness can cause an initially laminar flow to transition. Discrete roughness …
distributed roughness can cause an initially laminar flow to transition. Discrete roughness …
Hypersonic boundary-layer instabilities due to near-critical roughness
BM Wheaton, SP Schneider - Journal of Spacecraft and Rockets, 2014 - arc.aiaa.org
Measurements of instability and transition were obtained in the wake of a cylindrical
roughness within the laminar nozzle-wall boundary layer of the Purdue Mach-6 Quiet …
roughness within the laminar nozzle-wall boundary layer of the Purdue Mach-6 Quiet …
Hypersonic boundary-layer transition forced by wall injection: A numerical study
The laminar-turbulent transition of a Mach 4.6 flat-plate boundary layer forced by a wall
underexpanded jet is investigated using implicit large-eddy simulation based on a fifth-order …
underexpanded jet is investigated using implicit large-eddy simulation based on a fifth-order …
Coherent structures in the flow field generated by rigid flapping wing in hovering flight mode
Galilean invariant vortex identification methods and proper orthogonal decomposition (POD)
are used to capture the coherent structures (CS) in the flow field generated by rigid wing in …
are used to capture the coherent structures (CS) in the flow field generated by rigid wing in …
Unsteady motion in the supersonic flow over a wall-mounted hemisphere
Experiments were performed within Rutgers University's Mach 3.4 wind tunnel to visualize
the unsteady flow over a wall-mounted hemisphere using high-speed schlieren imaging and …
the unsteady flow over a wall-mounted hemisphere using high-speed schlieren imaging and …
Roughness-induced instabilities in a Mach-6 laminar boundary layer
BM Wheaton - 2012 - search.proquest.com
To develop improved methods of transition prediction for isolated roughness, based on the
growth of disturbances in the roughness wake, the underlying insta-bility mechanisms must …
growth of disturbances in the roughness wake, the underlying insta-bility mechanisms must …