Results 181 to 190 of about 4,282 (226)

Computations of inlet/isolator for SCRAMjet engine

Journal of Thermal Science, 2000
The inlet/isolator is one of the important parts to the SCRAMjet engine. In the present paper, the flow fields within an inlet and isolator of a SCRAMjet engine have been simulated by the Reynolds-Averaged Navier-Stokes equations with the Baldwin-Lomax algebraic turbulence model. The second order H. C. Yee TVD scheme is used for the inviscid flux terms
Xiaodong Wang, Jialing Le
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Pulsejet, Ramjet, and Scramjet Engines

2016
This chapter handles the first group of jet engines, namely, Ram-Based Engines, which includes pulsejet, ramjet, and scramjet engines. All the three types are composed of three stationary modules, namely, intake (or inlet), combustion chamber, and nozzle.
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Simulation of an airframe-integrated scramjet engine

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
A simulation model of the airframe-integrated scramjet engine was constructed for the system study and the preliminary design of the aerospace plane. It contained not only the engine itself, but also the cooling system, the fuel supply system, and a part of the airframe, which was also a part of the engine and affected the engine performances.
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Scramjet Engines: The First Forty Years

Journal of Propulsion and Power, 2001
Ageneralreviewoftheemergenceandmaturingofsupersoniccombustionramjet (scramjet)enginetechnologies overthelast 40 years is presented. The review isgiven in terms of theeffortscompleted or proceeding in theUnited States, Russia, France, Germany, Japan, Australia, and other countries.
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Preliminary analysis of scramjet engines based on engineering models

Aerospace Science and Technology, 2015
Abstract A mathematical model for analyzing two-dimensional scramjets was developed. The inlet was modeled with the oblique shockwave relationships. The combustor and nozzle were treated with quasi-one-dimensional flow assumption and finite rate chemistry was also considered for hydrogen–air combustion, with a separate mixing model.
Tiago C. Rolim, Paulo G.P. Toro
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Shock interference heating in scramjet engines

2nd International Aerospace Planes Conference, 1990
Experimental and analytical research sponsored by the NASA Langley Research center and the NASP Structures Technology Maturation Program to define critical aerothermal loads for the NASP engine is summarized. Presented is a review of (1) shock-shock interaction on the engine cowl leading edge that results in a supersonic jet impinging on the leading ...
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Flow Physics Inside a Shape-Transitioning Scramjet Engine

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012
Rectangular-to-Elliptical Shape Transition (REST) scramjet engines show promise as an access-to-space technology, due to its desirable on- and off-design performance. However, a Mach 12 REST engine will require signicant improvements to its combustion efficiency to be useful as a part of a hybrid launch system.
Barth, James E., Wheatley, Vincent, Smart, Michael K., Petty, David J., Basore, Kevin D.   +4 more
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Cowl and Cavity Effects on Mixing and Combustion in Scramjet Engines

Journal of Propulsion and Power, 2011
To investigate the supersonic combustion patterns in scramjet engines, a model scramjet engine was tested in the T4 free-piston shock tunnel. The test model had a rectangular intake, which compressed the freestream flow through a series of four shock waves upstream of the combustor entrance.
Kang, San Hung, Lee, Yang Ji, Yang, Soo Suek, Smart, Michael K., Suraweera, Milinda V.   +4 more
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Design of scramjet engine fuel feed system scheme

2013 10th International Conference on Ubiquitous Robots and Ambient Intelligence (URAI), 2013
Scramjet is the basis for future hypersonic vehicles, and fuel supply system is an important part in scramjet engine development. Considering of the fuel active cooling, a fuel feed system scheme through valve control was analyzed and designed, and then the control program was put forward for this corresponding scheme.
Yuhuan Du, Xiaodong Zhang 0028
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Full Flow-Path Optimization of Axisymmetric Scramjet Engines

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2011
Scramjet propulsion is a hypersonic airbreathing technology that offers the great potential for economical and flexible access to space and high-speed atmospheric transport. This paper presents the results and physical insight obtained in a design optimization study conducted for axisymmetric scramjet engines.
Ogawa, Hideaki, Alazet, Yohan, Pudsey, Adrian, Boyce, Russell, Isaacs, Amitay, Ray, Tapabrata   +5 more
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