A brief account of some unrecorded techniques for flow visualization in flight for locating (a) boundary-layer transition at altitude, (b) shock-wave ... Research Council. Current papers, no. 1090) e-book
by Wellington Edrington Gray
by Wellington Edrington Gray. Published 1970 by . Stationery Off. in London Library of Congress.
by Wellington Edrington Gray. in London. Boundary layer, Shock waves.
By Wellington Edrington Gray Wellington Edrington Gray .
Visualization of In-Flight Flow Phenomena Using Infrared Thermography. Initial data acquired with the system indicated that IR thermography was a very promising tool for flow visualization. The presence of fixed pattern noise and other.
Obtaining high quality flow visualization results is, in many ways, more of an art than a science, and experience plays a key deciding role. The depth and breadth of the material will make this book invaluable to readers of all levels of experience in the field. Smoke plume visualization on a hovering hum- mingbird was used to reconstruct the near-field three-dimensional flow structure in the downwash. Yet, these visualization methods only depict pat- terns of streak-lines in the unsteady flow, leaving the vortex structures to be later interpreted from the complex smoke patterns.
KEYWORDS: Main subjects: boundary-layer transition, flow . probes were located near the leading edge of the test article and one was located on the apex of the pylon splitter plate.
KEYWORDS: Main subjects: boundary-layer transition, flow visualization Fluid: high speed flows, flows with shocks Visualization method(s): infrared thermography Other keywords: image processing, turbulence. ABSTRACT: A flight experiment was conducted to investigate the pressure distribution, local-flow conditions, and boundary-layer transition characteristics on a large flat plate in flight at supersonic speeds up to Mach . Boundary-layer transition was captured using an onboard infrared imaging system.
A passive control method for supersonic boundary-layer transition on a swept wing using longitudinal roughness is proposed
A passive control method for supersonic boundary-layer transition on a swept wing using longitudinal roughness is proposed . A passive control method for supersonic boundary-layer transition on a swept wing using longitudinal roughness is proposed. Tests were carried out to examine the effect of distributed roughness on the development of flow peturbations and on the laminar-turbulent transition. The method makes it possible to manipulate the transition in a wide range, bringing it either closer to the leading edge of the wing by 30 % or delaying it by 40%. Keywords.
The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG).
This briefing note refers to the findings of the most recent study, carried out in 2005 for EUROCONTROL by the Dutch .
This briefing note refers to the findings of the most recent study, carried out in 2005 for EUROCONTROL by the Dutch National Aerospace Laboratory (NLR)1. This briefing note is the first of a series of five2 which address the main factors affecting pilot-controller voice communications. It provides an overview of these factors and makes some general recommenda-tions. There is also a short section dealing with emergency communications.
The shock wave was deeply entrained in the boundary layer and was highly distorted by passing large turbulent structures for several boundary layer thicknesses downstream of the corner. The 10 sharp fin interaction revealed the quasiconical symmetry of this type of interaction. ark:/13960/t6355gr0n.
is a boundary layer thickness but it is constant . On the calculation of steady flow in the boundary layer near the surface of a cylinder in a stream.
is a boundary layer thickness but it is constant(vorticity generated at the solid surface is prevented diffusing far away by an opposing convection, similar profiles are Blasius boundary layer with suction, Von Kármán swirling flow et. ). Drazin, Philip . and Norman Riley. The Navier–Stokes equations: a classification of flows and exact solutions.