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Tuesday, August 4, 2020 | History

3 edition of Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet found in the catalog.

Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet

James T. Walton

Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet

by James T. Walton

  • 223 Want to read
  • 29 Currently reading

Published by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Airplanes -- Ramjet engines.,
  • Supersonic planes.

  • Edition Notes

    StatementJames T. Walton.
    SeriesNASA technical memorandum -- 4376., NASA technical memorandum -- 4376.
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14687585M

    Publication of a survey of the combustion problems in propulsion today (e.g. flame-holding problems at high velocity). 2. Preparation of a survey of the fundamental problems in combustion, emphasising their aerothermodynamic aspects. 3. Preparation of a roster of research scientists concerned with the problems of combustion. For sale by the Superintendent of Documents, U.S. Government Printing Of f ice Internet: book Phone: toll f ree () ; DC area () Fax: () Mail: Stop IDCC, Washington, DC ISBN Y E A R S Steven J. Dick Editor NASA SP


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Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet by James T. Walton Download PDF EPUB FB2

Get this from a library. Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet. [James T Walton; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.]. Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet [microform] / J Progress toward synergistic hypermixing nozzles [microform] / D.O.

Davis and W.R. Hingst Heat pipe cooling for scramjet engines [microform] / Calvin C. Silverstein. The unique component flow phenomena is discussed of the airframe-integrated supersonic combustion ramjet (scramjet) in a format geared towards new.

NASA Technical Reports Server (NTRS) Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet Nov 1, 11/92 by NASA Technical Reports Server (NTRS).

Figure Propulsion-airframe integrated scramjet with station numbering. 27 Figure Types of supersonic air inlets. 29 Figure Schematic of flow structure in. The scramjet (supersonic combustion ramjet) is an air-breathing engine with the supersonic flow at the combustor entrance, i.e., with essentially lower deceleration of flow in the inlet with.

A SUPERSONIC THROUGH-FLOW FAN ENGINE AIRFRAME INTEGRATION STUDY Paul J. Barnhart* Sverdrup Technology, Inc. NASA Lewis Research Center Group Cleveland, Ohio ABSTRACT A study is undertaken to investigate the engine airframe integration effects for supersonic through-flow fan engines installed on a Mach supersonic cruise vehicle.

The focus is on the phenomena that dictate the thermo-aerodynamic processes encountered in the scramjet engine, including component analyses and flowpath considerations; fundamental theoretical topics related to internal flow with chemical reactions and non-equilibrium effects, high-temperature gas dynamics, and hypersonic effects are included.

Full text of "DTIC ADA The Hypersonic 2. From Scramjet to the National Aero-Space Plane" See other formats. This results in a combined cycle engine turbo-ramjet.

Having turbomachinery work output independent of Mach number leads to ATR engine. At flight speeds > Machpressure losses in decelerating supersonic flow to subsonic speeds for combustion are too high.

This is overcome by burning fuel in a supersonic stream scramjet 6. Chan, W.Y.K., Mee, D.J., Smart, M.K., Turner, J.C.: Effects of flow disturbances from cross-stream fuel injection on the drag reduction by boundary layer combustion. In: AIAApresented at the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, Tours, France (), 24–28 Sept Google ScholarCited by: 4.

Investigation of three-dimensional flow field in a turbine includingrotor/stator interaction. II - Three-dimensional flow field at the exit of the nozzle M.

ZACCARIA and. Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C.

Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. "A Study of the Motion and Aerodynamic Heating of Bal­listic Missiles Entering the Earth’s Atmosphere at High Supersonic Speeds,’ NACA TR-1 (1 ); H. Julian Allen, "The Aerodynamic Heating of Atmospheric Entry Vehicles,’ in J.

Gordon Hall, ed., Fundamental Phenomena in Hypersonic Flow: Proceedings of the International Symposium. FIG AIRFRAME INTEGRATED SUPERSONIC COMBUSTION RAMJETS __.__ Fig Illustrates In more detail the possible geometries that emerge for a scramjet as a result of integration of the intakc and the supersonic combustor combined with need wherever possible to.

keep all leading edges swept. DVIR-UXDIR TUJETlRAWAET UZZC1zm MACH0 5/5(1). Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.

NASA Historical Data Book Vol. 8 - Free ebook download as PDF File .pdf), Text File .txt) or read book online for free. NASA earth science and space applications, aeronautics,technology and exploration, tracking and data acquisition/space operations, facilities and 5/5(1).

Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet. NASA Technical Reports Server (NTRS) Walton, James T. The unique component flow phenomena is discussed of the airframe-integrated supersonic combustion ramjet (scramjet) in a format geared towards new players in the arena of hypersonic.

The Ramjet and the Supersonic Combustion Ramjet (Scramjet) Engine Cycle An invention attributed to Rene´ Lorin of France in (Hallion, ), the ramjet is a remarkable air-breathing engine in its conceptual simplicity.

In many cases, the authors have integrated these tools to allow data, including large combustion data sets, to flow seamlessly, for example, from modeling tools to data archives.

In this paper the authors describe the work of a larger collaborative effort to design, implement and deploy the DCC.«less. Supersonic Combustion Ramjet Research. Introduction Background A scramjet (supersonic combustion ramjet) engine is an air-breathing jet engine in which combustion takes place in supersonic airflow.

As in ramjets, a scramjet relies on high vehicle speed to forcefully compress and decelerate the incoming air before combustion (hence ramjet).While axisymmetric engines were tested, the modular two-dimensional airframe-integrated supersonic combustion ramjet (SCRJ) engine emerged as the candidate of choice for many missions.

This configuration permits development in reasonable size ground facilities, and requires a relatively modest flight test vehicle for a single module testing.The real key to [the swept wing] was to get subsonic flow at supersonic speed by getting the wing inside the Mach cone the development of what I would say [was] the really correct sweep theory for supersonic speeds occurred in Germany in ’43 or ’44, and with me in ” (See transcript of Jones-Bonney interview, p.

6).