2 edition of Hypersonic boundary layers and flow fields found in the catalog.
Hypersonic boundary layers and flow fields
North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel.
|Series||AGARD conference proceedings,, no. 30|
|Contributions||Royal Aeronautical Society.|
|LC Classifications||TL574.B6 N66|
|The Physical Object|
|Pagination||1 v. (various pagings)|
|LC Control Number||72403861|
This book contains the papers presented at the West East High Speed Flow Fields (WEHSFF_) conference held in Marseilles (France) during the period April This conference was in connection with the third European FloWnet (Flow Library Over the Web network) data base workshop. Flow field reconfiguration and drag reduction have been investigated by numerically solving Navier-Stokes equations, with the 2nd order dispersion controlled dissipative scheme adopted for the convective term discretion and the 2nd order central difference scheme for viscous term. Spikes and sideward jets nearby the spike noses were set up in the front of the blunt body to reconfigure the flow.
Receptivity and stability of hypersonic boundary layers are numerically investigated for boundary layer flows over a 5-degree straight cone at a free-stream Mach number of To compute the shock and the interaction of shock with the instability waves, we solve the . A high-order finite difference method is employed to simulate the hypersonic flow field to analyze the evolution of the disturbance wave in the hypersonic boundary layer and to investigate the effect of roughness on receptivity of the boundary layer.
Following the achievement of a man made vehicle attaining hypersonic speeds in the late 's, hypersonic flow quickly became a field great interest. Early on, in the 50's and 60's, analytic methods for hypersonic flow were developed by early pioneers of the field, but by the late 60's and into the 70's these methods began to be overshadowed by CFD : Sampson Kristmann Davis. The linear instability and breakdown to turbulence induced by an isolated roughness element in a boundary layer at Mach $2. 5$, over an isothermal flat plate with laminar adiabatic wall temperature, have been analysed by means of direct numerical simulations, aided by spatial BiGlobal and three-dimensional parabolized (PSE-3D) stability analyses.. It is important to understand transition in.
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In addition, the book presents useful equations for calculating heat transfer between reacting gas boundary layers and reacting, melting, sublimating, and otherwise decomposing surfaces. Designed for advanced undergraduate and graduate engineering courses in modern boundary-layer theory, this volume also serves as a valuable reference for professionals.4/5(2).
The balance of this book beyond the present chapter is devoted to the details Hypersonic boundary layers and flow fields book hypersonic or reacting boundary-layer theory.
It is the purpose of the present chapter to provide a less detailed, broader description of the "hypersonic heating problem" and its : Dover Publications. His book, Hypersonic Flow Theory, co-authored with Wallace D. Hayes, and reprinted by Dover in as Hypersonic Inviscid Flow, is still the basic book on this subject.
Synthetic Fuels, written with R. Edwin Hicks, is certainly one of the most important and timely engineering texts ever reprinted by Cited by: Viscous hypersonic flow: theory of reacting and hypersonic boundary layers | Dorrance, William H | download | B–OK.
Download books for free. Find books. hypersonic speeds, however, the boundary layers are much thicker compared to those at low speeds. Also the effects of the boundary layer on the external flow are more pronounced, and often these must be taken into account in determining the flow in the boundary layer itself.
Thus the corner problem can no longer be ignored,File Size: 3MB. Hypersonic Flow Theory presents the fundamentals of fluid mechanics, focusing on the hypersonic flow theory and approaches in theoretical aerodynamics.
This book discusses the assumptions underlying hypersonic flow theory, unified supersonic-hypersonic similitude, two-dimensional and axisymmetric bodies, and circular cylinder.
Mach number in boundary layer flow (by experiment). Figures from , where original references are given. Figure 2. Integral scale as a function of freestream Mach number in boundary layer flow (by experiment). Open symbols: subsonic flow. Closed symbols: supersonic and hypersonic flow. Figure from , where original references are given.
The location of a boundary layer transition varies with a large number of factors, including the vehicle shape, altitude, orientation of vehicle, materials of the vehicle, its surface texture, temperature of the surface, Mach number and Reynolds number, which is the ratio of inertial forces to viscous forces in the air flow.
Hypersonic flows are flow fields where the fluid velocity is much larger than the velocity of propagation of small disturbances, the velocity of sound. Transition and turbulence production in hypersonic boundary layers have recently received considerable attention owing to their fundamental importance and strong relevance to the safety of hypersonic vehicle flight, including significant increase in aerodynamic heating, entropy production, and drag.
1,2 1. Fedorov, Annu. Rev. Fluid Mech. 43, 79 (). Boundary Layer Control for Hypersonic Airbreathing Vehicles Scott A. Berry,* Robert J. Nowak,* and Thomas J. Horvath* NASA Langley Research Center, Hampton, VA, Active and passive methods for tripping hypersonic boundary layers have been examined in NASA Langley Research Center wind tunnels using a Hyper-X model.
This investigation. Hypersonic boundary layers and flow fields; papers presented at a Specialists' Meeting of the Fluid Dynamics Panel of AGARD held at the Royal Aeronautical Society, London, May, Author: North Atlantic Treaty Organization.
An experimental and theoretical investigation of instabilities in hypersonic flat plate boundary layer flow Physics of Fluids, Vol. 7, No. 4 Quiet-flow Ludwieg tube for high-speed transition research. Get this from a library. Flow-field and drag characteristics of several boundary-layer tripping elements in hypersonic flow.
[Allen H Whitehead, Jr.; United States. National Aeronautics and Space Administration.; Langley Research Center.] -- Flow field and drag characteristics of several laminar boundary layer tripping element in hypersonic flow.
Flow 1: M = ; Flow 2: M = ; Flow 3: M = ; Flow 4: M = (b) Integral scale as a function of friction Mach number in boundary layer flow (by experiment). Hypersonic Turbulent Skin-Friction and Boundary-Layer Profiles on Nonadiabatic Flat Plates. Evaluation of equilibrium turbulence for a naturally developing hypersonic boundary layer at nonadiabatic wall conditions.
Turbulent boundary layer flow separation measurements using holographic interferometry. Delery, “Shock/shock and shock wave/boundary layer interactions in hypersonic flows,” in Aerothermodynamics of Hypersonic Vehicles, AGARD Report No. AGARD‐R‐, Google Scholar 9. Goldstein  has given a solution to the boundary-layer equations for the flow just downstream from the trailing edge of a flat plate.
It is shown here that this approximation is no longer valid i. However due to thin shock layer where boundary layer thickness and shock layer thickness are comparable, complexity of flow field increases.
Viscous Interaction. The no-slip property of the viscous fluid flow causes boundary layer formation near the wall. Such boundary layer formation leads to huge loss of kinetic energy at hypersonic speeds.
Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers Article in AIAA Journal 47(9) September with 59 Reads How we measure 'reads'. Numerical and experimental investigation into hypersonic boundary layer transition induced by roughness elements.
But the numerical simulation provides more details of flow field, which can distinguish clearly the high and low Q w value regions in the by: 2.Secondary Instabilities of Görtler Vortices in High-Speed Boundary Layers Mechanisms and Flow Control on Laminar-Turbulent Transition.
Authors: Ren, Jie Free Preview. Nominated by the Tsinghua University China as an outstanding thesis in the field Stabilization of the Hypersonic Boundary Layer.
Pages Ren, Jie.For compressible flow (or flow at high speeds), however, increasing flow temperature (due to friction heat) near the body surface causes the boundary layer to become thicker as speed increases. The two primary factors driving this boundary layer growth are an increase in .