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2 edition of Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds found in the catalog.

Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds

Davis H Crawford

Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English

    Subjects:
  • Fluid mechanics

  • Edition Notes

    StatementDavis H. Crawford
    SeriesNASA technical memorandum -- 80115
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
    The Physical Object
    Pagination38 p. :
    Number of Pages38
    ID Numbers
    Open LibraryOL14925624M

    Re: Russia, US and other developments in Hypersonic Research max steel on Fri pm Australia and partners Boeing, BAE Systems and DLR (German Aerospace Center) have a successful mach hypersonic missile test. Aerodynamics, from Greek ἀήρ aero (air) + δυναμική (dynamics), is the study of motion of air, particularly as interaction with a solid object, such as an airplane wing. It is a sub-field of fluid dynamics and gas dynamics, and many aspects of aerodynamics theory are common to these term aerodynamics is often used synonymously with gas dynamics, the difference being that. With a $20 million U.S. Department of Energy grant, Stanford researchers plan to use some of the world's fastest supercomputers to model the complexities of hypersonic flight, focusing on how fuel and air flow through a scramjet engine. Aeronautical engineers believe hypersonic planes flying at s. Re: Russia, US and other developments in Hypersonic Research max steel on Mon pm I've reas your links the one sputnik quotes is calling Yu as Yu so it's pretty much evident there is only glider not TWO.

    This proceedings present the results of the 29th International Symposium on Shock Waves (ISSW29) which was held in Madison, Wisconsin, U.S.A., from July 14 to J It was organized by the Wisconsin Shock Tube Laboratory, which is part of the College of Engineering of the University of.


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Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds by Davis H Crawford Download PDF EPUB FB2

Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.

The theoretical region of overlap for the two types of interaction was investigated by observing in the Schlieren system of the Langley inch hypersonic flow apparatus the intersection of oblique shocks generated by two sharp 10 degree wedges as the wedge angles of.

The theoretical region of overlap for the two types of interaction was investigated by observing in the Schlieren system of the Langley inch hypersonic flow apparatus the intersection of oblique shocks generated by two sharp 10 degree wedges as the wedge angles of Author: D.

Crawford. Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds / By Davis H. Crawford, Langley Research Center. and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch. Abstract. Subject category "October "--Cover."Langley Research Center."Includes.

Singh, D.J., Kumar A. & Tiwari, S.N. Influence of shock-shock interactions on the blunt body flow field at hypersonic flight speeds. AIAA 7th Applied Aerodynamics Conference Cited by: 8.

Shock-wave-turbulent-boundary-layer interaction and its control: A survey of recent developments. Abstract. This paper presents an overview of some of the recent developments that have taken place in the understanding, prediction and control of two-dimensional shock-wave-turbulent-boundary-layer interaction at high by: Shock waves in supersonic fluid flows are discontinuities that change the entire flow characteristics owing to their own existence and their interaction with other fluid dynamic phenomena.

These interactions will induce unwanted aerodynamic forces on bodies moving with supersonic and hypersonic speeds and unpredictable fluid dynamicFile Size: KB.

This article is devoted to an experimental and numerical study of shock wave/boundary layer interaction in hypersonic laminar flow (M = 10). The experiment was performed in the ONERA R5Ch wind. developments that have taken place in the understanding, prediction and control of two-dimensional shock-wave-turbulent-boundary-layer interaction at high speeds.

Following a brief description of the upstream influence phenomena, detailed discussions of incipient and fully.

Through some classical hypersonic applications in recent years, such as the shock/shock interaction, shock wave/boundary layer interaction, and hypersonic boundary layer separation problems, the. AGARD Working Group 18 (WG18) examined the Computational Fluid Dynamics (CFD) capability for prediction of 2-D and 3-D shock wave laminar and turbulent boundary layer interactions for three generic configurations: single fin (Fig.

2a), double fin (Fig. 2b) and hollow cylinder flare (Fig. 2c) [1].Cited by: The two p01nts of shock 1ntersect10n are connected by a strong shock as shown in f1g­ ure 1 (b). The two p01nt-shock 1nteraction patterns are al1ke 1n that they are composed of a strong shock 1ntersect1ng w1th an obl1que shock and w1th the oblique shock reflect1ng from the shear layer trang the p01nt.

from transonic aircraft wings to hypersonic vehicles and engines. A comprehensive survey of the interac-tion of shock wave and turbulent boundary layer was published by Viswanath in [20]. In his paper, an overview of some developments in understanding, prediction, and control of two-dimensional SBLI at high speeds was presented.

A general Cited by: 8. At a flight velocity of 40, ft/sec at the outer part of the wake, temperature may reach °K at 50– diameters behind the body [ 17]. A typical turbulent wake behind a blunt body, an intermediate body, and a slender body at hypersonic speeds is shown in Figs.

18 and than half a century analysts have defined hypersonic speeds as Mach 5 and higher.4 Only rocket-powered craft have flown so fast—and Mach 5 defines only the lower bound of the hypersonic regime.

An important range of hypersonic speeds extends from Mach 20 to 25 and includes the velocities of long-range ballistic missiles and. Davis H. Crawford has written: 'Some recent developments in the prediction of shock interaction phenomena at hypersonic speeds' -- subject(s): Fluid mechanics Asked in Food Coloring How much food.

Boundary layer interaction phenomena become important in hypersonic flow. The new features of a physical or chemical nature appearing here are mostly connected with the high temperatures generally associated with the extremely strong shock waves present in such flows as.

A REVIEW OF SOME RECENT DEVELOPMENTS IN HYPERSONIC FLOW**This work was supported by the United States Air Force through the Office of Scientific Research, Air Research and Development Command, under Contract AF 49 (), and through the Aeronautical Research Laboratory of Wright Air Development Center, under Contract No.

33 () ARFL ARI 23 November Critical Hypersonic Aerothermodynamic Phenomena John J. Bertin1,2 and Russell M. Cummings2 1 Department of Mechanical Engineering and Materials Science, Rice University, Houston, Texas ; email: [email protected] 2.

investigating unsteady phenomena and there is only brief mention of the recent developments of shock-tube techniques for the study of steady-flow conditions in the hypersonic regime. The development of ‘hot shot’ and light gas gun tunnels for the investigation of hypersonic. Recently, there have been significant advances in the fields of high-enthalpy hypersonic flows, high-temperature gas physics, and chemistry shock propagation in various media, industrial and medical applications of shock waves, and shock-tube technology.

This series contains all the papers and. hypersonic vehicles. Research works in this field were collected and compiled nicely in the famous book “Shock Wave Reflection Phenomena” by Prof. Ben-Dor in Ben-Gurion University of Negev, Israel. The course is planned based mainly on this book and other recent works being pursued in this area.

Hypersonic Aerodynamics Introduction Hypersonic vehicles are commonplace. There are many more of them than the supersonic aircraft discussed in the last chapter. Applications include missiles, launch vehicles and entry bodies. A huge effort has been made developing hypersonic aerodynamics methods and Size: 1MB.

The flow phenomena in the strong and weak interaction regions at the leading edge of the hypersonic plate problem are of paramount importance to this analysis. Because of the inherent complexity of the flow physics, analytical models are scarce, and reliable analyses can only be obtained exclusively by experiments and numerical by: 2.

control,materials,shock interaction,hypersonic tur-bulentboundary layer,skinfriction,reactioncontrol jets,aerodynamic heating,and heat transfer. The SandiaNationalLaboratory (Albuquerque,New Mexico) vehiclesprovided much oftheaerothermody-namic data obtained during the 'sand 's.s These data have provided new insightsintothe un-File Size: 1MB.

Hypersonic flow structure in a large-scale multi-diaphragm shock tube Fluid Dynamics, Vol. 28, No. 5 Turbulent boundary-layer characteristics over a flat-plate/wedge configuration at Mach 6. There have been protests in Brazil in recent years due to the amount of money being spent by the government on the World Cup and Olympics, while there is.

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.

Flow prediction in the shock/boundary-layer interaction region, identified in Fig. 1, is the primary focus of this work. Modelswithtwoflareangles,30and36,weretestedattwoMach numbers (nominally, 11 and 13), resulting in four test cases.

The freestream and geometric. Airframe-propulsion integration design is one of the key techniques of air-breathing hypersonic vehicles [] to reduce overall drag and achieve positive thrust margins at hypersonic speeds [].The engine and airframe aerodynamics therefore become highly coupled [].Airframe-propulsion integration methodologies for the hypersonic vehicle have been extensively studied by many researchers [4, 5, 6, 7].Author: Yao Zheng, Shuai Zhang, Tianlai Gu, Meijun Zhu, Lei Fu, Minghui Chen, Shuai Zhou.

Welcome to the NASA's Guide to Hypersonics: Hypersonic aerodynamics is a special branch of the study of aeronautics. The chief characteristic of hypersonic aerodynamics is that the temperature of the flow around the aircraft is so great that the chemistry of the gas must be considered.

At low hypersonic speeds, the molecular bonds vibrate, which changes the magnitude of the forces. This book is the second edition of a successful, self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics.

Like the first edition, it assumes no prior familiarity with either subject on the part of the reader/5(36). Auckland, New Zealand December Aerothermodynamics of Hypersonic Shock Wave Boundary Layer Interactions N.

Deepak, S. Gai and A. Neely School of Engineering & IT High Speed Flow Group UNSW, Australian Defence Force Academy CanberraAustralia Abstract Hypersonic laminar flow past a 24 compression corner has.

Oblique-shock relations for air in chemical equilibrium have been calculated for flight velocities up to 25, feet per second at altitudes up tofeet. Results show that those shock parameters which are functions only of Mach number normal to the shock for an ideal gas are strongly influenced by flight altitude (initial conditions), as.

Nozzle Description. In Table Table1, 1, the conditions for the TBCC exhaust system design point are on the total inflow parameters of the ramjet nozzle, the ramp and flap contour at the design point of Mach 4 (cruise Mach number, H = 28 km) in ramjet mode was obtained by the MOC [], as shown in Fig.

2(b).On the basis of this design point, the nozzle had an overall area ratio of Cited by: 9. Lind and M. Lewis, “A numerical study of the unsteady processes associated with the Type IV shock interaction,” AIAA Paper No. 93–, Google Scholar; 8. Delery, “Shock/shock and shock wave/boundary layer interactions in hypersonic flows,” in Aerothermodynamics of Hypersonic Vehicles, AGARD Report No.

AGARD‐R Cited by: Harvey, J.K., Holden, M.S. and Wadhams, T.P. Code validation study of laminar shock/boundary layer and shock/shock interactions in hypersonic flow Part B: Comparison with Navier-Stokes and DSMC solutions,AIAA, 39th Aerospace Sciences Meeting and Exhibition, 8 Cited by: 4.

@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. Understanding hypersonic aerodynamic heating processes caused by drag could lead to better leading edge shapes and materials to deal with the heat and pressure.

UAH is already involved in aerodynamic testing of engine intake shock wave phenomena at supersonic speeds. Figure 1. Interactions between aerothermodynamics and other disciplines the high-temperature effects typical for higher speeds and altitudes, by means of high-enthalpy or hot-flow facilities.

ESA has supported the modernisation of existing cold wind tunnels, and also the construction of facilities with new. hypersonic tunnel which was this country's first hypersonic facility, conceived and proposed inand operated successfully at Mach for the first time in Our Gas Dynamics Laboratory, which contained several hypersonic nozzles, came into operation a few years later, in the early '50' Size: 9MB.

Shock Wave-Boundary-Layer Interactions - Ebook written by Holger Babinsky, John K. Harvey. Read this book using Google Play Books app on your PC, android, iOS devices. Download for offline reading, highlight, bookmark or take notes while you read Shock Wave-Boundary-Layer Interactions.This book is the second edition of a successful, self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics.

Like the first edition, it assumes no prior familiarity with either subject on the part of the reader. If you have never Price: $