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
|Statement||James T. Walton.|
|Series||NASA technical memorandum -- 4376., NASA technical memorandum -- 4376.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.|
|The Physical Object|
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.