Wave-interactions in supersonic and hypersonic flows



Publisher: Old Dominion University Research Foundation, Publisher: National Aeronautics and Space Administration, Publisher: National Technical Information Service, distributor in Norfolk, Va, [Washington, DC, Springfield, Va

Written in English
Published: Downloads: 305
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Subjects:

  • Aerodynamics, Supersonic.,
  • Waves.

Edition Notes

Disagree: Each of these article (supersonic and hypersonic flows) can be expanded further. Also many effect of hypersonic flow are not applicable for supersonic flow. I am not sure of the transonic flow article, maybe that can be merged with supersonic flows, but would to know what others have to say about that. myth , 10 September (UTC). Shock-wave/boundary-layer interactions continue to be ubiquitous phenomena in supersonic and hypersonic aerodynamics, and their importance is often critical as, for example, for hypersonic controls and for air intakes in general. This is the reason for the continuous research efforts in this field, aiming at developing reliable methodologies for future vehicle design. The supersonic jet interaction flow field generated by a sonic circular jet with a pressure ratio of exhausting into a turbulent MACH cross flow over a flat plate was investigated using numerical simulations. The simulations made use of the three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations coupled with Wilcox's k-ω turbulence model. Wallace D. Hayes (b. September 4, – d. March 2, ) was a professor of mechanical and aerospace engineering at Princeton University and one of the world's leading theoretical aerodynamicists, whose numerous and fundamental contributions to the theories of supersonic and hypersonic flow and wave motion strongly influenced the design of aircraft at supersonic speeds and missiles at.

Get this from a library! Special course on Shock-wave/boundary-layer interactions in supersonic and hypersonic flows = Interactions entre ondes de choc et couches limites dans les ecoulements supersoniques et hypersoniques. [North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel.; Von Karman Institute for Fluid Dynamics.;] -- . Counterflow drag reduction by supersonic jet for a large angle blunt cone at hypersonic Mach number is investigated in a shock tunnel. The flowfields around the test model in the hypersonic flow with an opposing supersonic jet emanating from the stagnation point of the model are visualized by high speed schlieren technique. The aerodynamic drag force is measured using the accelerometer based. @article{osti_, title = {Interaction of Electromagnetic Waves With Plasmas of Hypersonic Flows}, author = {Glick, Herbert S.}, abstractNote = {Problems involving the interaction of electromagnetic waves with the plasma sheath surrounding a hypervelocity vehicle lead to new and challenging areas of research. Communication blackout'' and the tasks of locating reentering ICBM . Besides shock wave interactions, compressible flows have additional dilatational effects and, due to the finite sound speed, pressure fluctuations are localized and modified relative to.

  The flow after the conical shock was supersonic or even hypersonic, which experienced a deflection on the blunt body shoulder and generated the reattached shock. The conical shock also interacted with the reattached shock, results in the formation of a . Transonic flows in astronomy and astrophysics. In astrophysics, wherever there is evidence of shocks (standing, propagating or oscillating), the flow close by must be transonic, as only supersonic flows form shocks. All black hole accretions are transonic. Many such flows . Get this from a library! The Mark IV Supersonic-Hypersonic Arbitrary-Body Program. Volume I. User's Manual.. [Arvel E Gentry; Douglas N Smyth; Wayne R Oliver; DOUGLAS AIRCRAFT CO LONG BEACH CA.;] -- The report describes a digital computer program system that is capable of calculating the supersonic and hypersonic aerodynamic characteristics of complex arbitrary three-dimensional . Two-dimensional (2D) and axisymmetric minimum length nozzles (MLNs) with constant and variable specific heat were strictly designed using the method of characteristics (MOCs). MOC is a numerical te.

Wave-interactions in supersonic and hypersonic flows Download PDF EPUB FB2

The impingement of shock waves on blunt bodies in steady supersonic flow is known to cause extremely high local heat transfer rates and surface pressures. Although these problems have been studied in cold hypersonic flow, the effects of dissociative relaxation processes are by:   The impingement of shock waves on blunt bodies in steady supersonic flow is known to cause extremely high local heat transfer rates and surface pressures.

Although these problems have been studied in cold hypersonic flow, the effects of dissociative relaxation processes are unknown. In this paper we report a model aimed at determining the boundaries of the possible interaction regimes Cited by:   The shock interaction in the crotch region creates a very complex flow-field and an uneven distribution of the surface heat flux.

An extremely high heat flux caused by a shock-wave/boundary-layer interaction, a shear layer attachment, or an impingement of the supersonic jets occurs over a narrow by: 6. Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; Standards; Other Publications.

Software/Electronic Products; Aerospace America ; Public Policy Papers ; ed by: Abstract. The extension of particle image velocimetry to supersonic and hypersonic wind-tunnel flows has been achieved in the last decade.

This was mainly possible with the advent of short interframing-time CCD cameras with temporal resolution allowing to obtain correlated particle images at flow velocities exceeding m∕ by:   I. Introduction. S hock interactions are known to produce high pressure Wave-interactions in supersonic and hypersonic flows book heat flux in the local interaction region on a vehicle’s surface and thus can severely shorten the useful life of the structural components [].Therefore, shock interaction heating is a major concern in the structural design of hypersonic vehicles.

Three-dimensional inward-turning hypersonic inlets [2 – 6] have been. Last night, SpaceX held another show and tell, and there was a nice long, almost 1 minute burn of a raptor engine. The flow stabilized really nicely, and you get an absolutely fantastic view of the. Molecular Physics and Hypersonic Flows bridges the gap between the fluid dynamics and molecular physics communities, emphasizing the role played by elementary processes in hypersonic flows.

In particular, the work is primarily dedicated Wave-interactions in supersonic and hypersonic flows book filling the gap between microscopic and macroscopic treatments of the source terms to be inserted in the fluid dynamics codes. Physical interactions between turbulence and shock waves are very complex phenomena.

If these interactions take place in chemically reacting flows, the degree of complexity increases dramatically. Examples of applications may be cited in the area of supersonic combustion, in which the controlled generation of turbulence and/or large scale vortices in the mixing and flame-holding zones is.

Misra, in Lightweight Composite Structures in Transport, Hypersonic air-breathing propulsion. Hypersonic vehicles fly faster than five times the speed of sound and can enable a new class of flight vehicles that enable faster access to space, rapid military response at long range, and faster means of commercial air travel.

Traditionally, rocket boosters have been used for. rated, supersonic interactions. The second class of interactions involved weak shocks impinging near small expansion corners.

As a prelude to studying this interaction, a hypersonic similarity parameter was identified for the pure, expansion corner flow. The expansion corner severely damped out surface pressure fluctuations. When a. Approximate calculation of the interaction of supersonic flow with a laminar layer in the flow separation region Fluid Dynamics, Vol.

1, No. 5 Theory of laminar near wake of blunt bodies in hypersonic flow. In a supersonic wind tunnel one technique currently employed for measuring the flow Mach number is the Pitot tube technique. The Pitot probe (see Fig.

), which is formed of a hollow small tube, is placed parallel to the flow supersonic flows, a detached bow shock wave is formed ahead of the probe. The tube is connected to a pressure transducer, which measures the. 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 : Wallace D. Hayes, Ronald F. Probstein. He has also written twelve hardcover books. Three of them– Colonies in Space (), Toward Distant Suns () and. The Man-Made Sun ()-have been alternate selections of the Book-of-the-Month Club.

His. Turbulent Skies (), a history of commercial aviation, is part of the Technology Book Series of the Alfred P.

Sloan Foundation. A small deflection in supersonic flow always takes place such that the flow properties are uniform along a front inclined to the flow direction.

Also, their only change is in the direction normal to the front, which is known as a wave. For small flow changes, the wave sets itself up at the Mach angle (µ) appropriate to the upstream flow. Get this from a library. Wave-interactions in supersonic and hypersonic flows.

[William D Lakin; Langley Research Center.]. When the component of free-stream velocity perpendicular to the leading edge is greater than the local speed of sound the wing is said to have a supersonic leading this case, as illustrated in Fig.there is two-dimensional supersonic flow over much of the wing, which can be calculated using supersonic airfoil the rectangular wing shown in Fig.the presence of a.

Characteristic Properties of Hypersonic Flows 4. Similarity Law for Limiting Hypersonic Flows Past Bodies of Given Shape Chapter II Hypersonic Flows Past Slender Bodies with Sharp Leading Edges 1. Estimate of the Disturbance Produced by the Supersonic Motion of Bodies in a Gas 2.

Similarity Law for Hypersonic Flows Past Slender Bodies 3. A shock wave is a surface of discontinuity propagating in a gas at which density and velocity experience abrupt changes.

One can imagine two types of shock waves: (positive) compression shocks which propagate into the direction where the density of the gas is a minimum, and (negative) rarefaction waves which propagate into the direction of maximum density.

WELCOME, LET THE FUN BEGIN. Get e-Books "Two Dimensional Separated Flows" on Pdf, ePub, Tuebl, Mobi and Audiobook for are more than 1 Million Books that have been enjoyed by people from all over the world. Always update books hourly, if not looking, search in the book search column.

Enjoy % FREE. supersonic flow and shock waves Download supersonic flow and shock waves or read online books in PDF, EPUB, Tuebl, and Mobi Format. Click Download or Read Online button to get supersonic flow and shock waves book now.

This site is like a library, Use. Characteristics of flow. While the definition of hypersonic flow can be quite vague and is generally debatable (especially due to the absence of discontinuity between supersonic and hypersonic flows), a hypersonic flow may be characterized by certain physical phenomena that can no longer be analytically discounted as in supersonic flow.

is in the supersonic formula. This illustrates how the situation in hypersonic flow is significantly different than the linear flow models at lower speeds. The Newtonian flow model can be refined to improve agreement with data. This form is known as the Modified Newtonian flow formula, () where the stagnation Cp max is a function of Mach.

Theory of laminar viscous-inviscid interactions in supersonic flow. Numerical Solutions of Supersonic and Hypersonic Laminar Compression Corner Flows. C.M. Hung and general theory and application to adiabatic boundary layer-shock wave interactions.

LEES and. The ISSW30 focused on the state of knowledge of the following areas: Nozzle Flow, Supersonic and Hypersonic Flows with Shocks, Supersonic Jets, Chemical Kinetics, Chemical Reacting Flows, Detonation, Combustion, Ignition, Shock Wave Reflection and Interaction, Shock Wave Interaction with Obstacles, Shock Wave Interaction with Porous Media.

Laminar separation in supersonic and hypersonic flows [Ginoux, Jean J] on *FREE* shipping on qualifying offers. Laminar separation in supersonic and hypersonic flows. The extension of particle image velocimetry to supersonic and hypersonic wind-tunnel flows has been achieved in the last decade.

This was mainly possible with the advent of short interframing-time CCD cameras with temporal resolution allowing to obtain correlated particle images at flow velocities exceeding m/s.

The most challenging aspects of PIV experiments in supersonic flows are still. Stanford Libraries' official online search tool for books, media, journals, databases, government documents and more.

Understanding of supersonic and hypersonic aerodynamics has matured since the s, and the goals of aerodynamicists have shifted from the behavior of fluid flow to the engineering of a vehicle such that it interacts predictably with the fluid flow.

Designing aircraft for supersonic and hypersonic conditions, as well as the desire to improve. History. The first manufactured object to achieve hypersonic flight was the two-stage Bumper rocket, consisting of a WAC Corporal second stage set on top of a V-2 first stage. In Februaryat White Sands, the rocket reached a speed of 8, km/h (5, mph), or approximately Mach The vehicle, however, burned on atmospheric re-entry, and only charred remnants were found.This paper presents PIV measurements obtained in Mach flowfields performed in the SJTU Hypersonic wind tunnel (HWT).

In order to certificate this technique, PIV experiments were conducted to the empty test section to provide uniform flow data for comparison with analysis data.

Dynamical properties of particle tracers were investigated to measure the particle response across an oblique.A hypersonic gun tunnel has been used to measure the heat-transfer-rate distribution over a compression corner under turbulent boundary-layer conditions.

Attached, incipient and separated flows .