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

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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.

Book details:

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

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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 > Mach , pressure 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: AIAA , presented 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.