Aerothermodynamic performance of mixed compression, shock-induced combustion ramjets.

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  • English
National Library of Canada , Ottawa
SeriesCanadian theses = -- Thèses canadiennes
The Physical Object
Pagination2 microfiches : negative. --
ID Numbers
Open LibraryOL17900095M
ISBN 100618076806

As one of the most promising propulsion systems in the future, shock-induced combustion ramjet engine can remedy the disadvantages in the integrated design of scramjet engine and airframe.

It can shorten the length of the combustor, lighten the structure weight of the engine and keep better performance in a broad range of flight Mach number. The elementary principle of shock-induced Cited by: tion wave combustion.

In the extreme fuel rich regions, combustion is inhi bi ted by the amount of fuel in the flow. Lean mixtures (Q Cited by: 2. Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine Article (PDF Available) in AIAA Journal 52(8) August with Reads.

from book High Performance Computing in Science and Engineering ’Transactions of the High Performance Computing Center, Stuttgart (HLRS) ). Papers presented at 10th results and review. Heiser, Pratt, and Dalyʼs book on hypersonic airbreathing propulsion contains a good overview of many propulsion concepts, which was followed by the study of injection strategies for ramjets by Riggins et al., a study of kerosene fuel combustion in supersonic flow, Billigʼs work on supersonic combustion ramjets, the study of scramjet Cited by: 9.

Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of. Full text of "DTIC ADA Ramjet and Ramrocket Propulsion Systems for Missiles Held at Monterey, California, London (United Kingdom), and Neubiberg (Germany F.

R.) on ; and September " See other formats. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A cumulative index to a continuing bibliography (supplement )" See other formats.

Combustion Performance of Hydrocarbon Fuel in a Dual-Mode Combustor. View Section, 3D Numerical Studies on Thrust Vectoring Using Shock Induced Self Impinging Secondary Jets.

View Section, Aerothermodynamic Cycle Model for New Hypersonic Propulsion: Rocket Ignited Supersonic Combustion Ram Jet. An investigation of the effects of incornplete fuel-air mixing in a mixed compression.

shock-induced combustion, rmjet (shcramjet) model w a s carried out. The variable equivalence ratio is applied to a planar, inviscid. chemicdy reacting, shcramjet flow- field. This flowfield is simulated numerically with a Lower-Upper Symmetric Gauss- Seidel (LU-SGS) scheme to solve the Euler equations at.

IGTI Combustion System Performance And Field Test Results Of The MSF Gas Turbine J.P. Claeys, K.M. Elward, W.J.

Description Aerothermodynamic performance of mixed compression, shock-induced combustion ramjets. PDF

Mick, R.A. Symonds, General Electric Company, Schenectady, NY, USA; GT IGTI TEMPER - A Gas-Path Analysis Tool For Commercial Jet Engines D.L. Doel, GE Aircraft Engines, Evendale, OH, USA; GT century (China) 4 the technology to convert the principals of rocket. Although Guillaume (Fr) patented a combined a.

turbomachinery. Historically, in-house capability has been balanced by a willingness to look outside of the Agency for management techniques that maintain cost, schedule, and performance discipline.

During the Apollo era, NASA executives turned to the U.S. Air Force for needed reforms, adopting large-scale systems management as their guiding managerial philosophy.5/5(1).

The goals were to build and test in flight a hypersonic research ramjet–scramjet engine using the X15A-2 research airplane that was modified to carry hydrogen as the fuel for the scramjet engine.

Two models were fabricated to test the structural engine integrity and to demonstrate the aerothermodynamic. Analysis of distortion data from TFP-3 mixed compression inlet test.

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NASA Technical Reports Server (NTRS) King, R. W.; Schuerman, J. A.; Muller, R. A program was conducted to reduce and analyze inlet and engine data obtained during testing of a TFP-3 engine operating behind a mixed compression usly developed distortion analysis techniques were applied to the.

Example Problems in LES Combustion.

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DTIC Science & Technology. AFRL-RW-EG-TP Example Problems in LES Combustion Douglas V. Introduction. There have been various studies related to a scramjet (supersonic combustion ramjet) engine as a candidate for use in hypersonic airplanes, or space planes,,.Since the combustion reactions of fuel jets should be occurring in supersonic airstreams in the scramjet combustor, stable combustion, or ignition and flameholding, of a fuel/air mixture, which Cited by: The interaction was formed by a deg compression corner, and the periodic blowing was introduced into the shock-induced separation bubble.

Measurements of the. 02 fluctuating mass flux and wall pressure were made, and the unsteady flowfield was visualized through stroboscopic schlieren videography. Although the control of the shock wave. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.

Among other 50th anniversary publications are a book of iconic images, America in Space: Space: NASA NASA’s ’s First Fity Fity Yea Years rs, ed. Steven J. Dick, Robert Jacobs, Constance Moore, Moor e, Anthony M. Springer, and Bertram Ulrich, foreword by Neil Armstrong (New York, NY: Abrams, ); a page 50th anniversary magazine.

NASA 50th ANNIVERSARY PROCEEDINGS NASA'S FIRST 50 YEARS HISTORICAL PERSPECTIVES Library of Congress Cataloging-in-Publication Data NASA's first 50 years: historical perspectives / Steven J. Dick, editor p. cm NASA SP.