Subsonic Combustion Ramjet Design


Book Description

This book presents a step-by-step methodology for the design of ramjet engines. It explores ramjet combustion, provides guidelines on how to size the engines, and discusses performance analysis. The book begins with an introduction to ramjet design, including fundamental definitions in the field. It then discusses ramjet engine performance, and fuels which can be used. Several types of ramjet engines are then explored, and guidelines for their design are presented, including flame holders, injectors, and combustors. Finally, the book concludes with a discussion of the types of materials which should be used for ramjet engines. This book is of interest to engine designers and engineers, researchers, and graduate students, as it collates research in a succinct, clear guide to the issue of designing ramjet engines.







Ramjet Engines


Book Description




THE UTILIZATION OF SUPERSONIC COMBUSTION RAMJET SYSTEMS AT LOW MACH NUMBERS.


Book Description

The low-speed performance of the supersonic combustion ramjet engine is investigated. A discussion of the fundamental problems of low-speed operation is followed by a review of techniques of converting from supersonic to subsonic combustion. A new engine concept, the 'dual-mode' engine, is discussed and its potential performance outlined.




The Scramjet Engine


Book Description

Demand for high-speed propulsion has renewed development of the supersonic combustion ramjet engine (Scramjet engine) for hypersonic flight applications.




RAMJET ENGINES.


Book Description

In this book the information on the theory, characteristics, construction, and design of subsonic and supersonic ramjet engines is based on domestic and foreign materials which have been published in the form of books and magazine articles. The theory of the basic elements of the engine - diffusers, combustion chambers, and jet nozzles -- is considered, as well as the operation of the entire engine. Molecular and even atomic fuels are regarded as sources of energy. This book is intended for engineers who are specialists in aircraft engine construction, and for students in higher educational aviation institutions who are familiar with the fundamentals of thermodynamics and gas dynamics.




Can-Type Combustor Design for a Low Cost Subsonic Ramjet Engine


Book Description

This study investigates the feasibility of using a low cost can combustor in a subsonic ramjet engine in the flight envelope of Mach 0.7 to 0.9, altitude 20,000 to 30,000 feet. A simple can combustor without close fabrication tolerances was designed and fabricated. The can was installed in a subsonic ramjet which was ground tested in a direct-connect pipe set-up. The combustion efficiency and thrust were determined at conditions representative of the flight envelope. These results are compared with results of a model subsonic ramjet engine cycle analysis. The end result of the program is a developed combustor system for a subsonic ramjet which is an inexpensive and attractive propulsion device for one-mission remotely piloted vehicles and target drones.




Hypersonic Airbreathing Propulsion


Book Description

An almost entirely self-contained engineering textbook primarily for use in undergraduate and graduate courses in airbreathing propulsion. It provides a broad and basic introduction to the elements needed to work in the field as it develops and grows. Homework problems are provided for almost every individual subject. An extensive array of PC-based user-friendly computer programs is provided in order to facilitate repetitious and/or complex calculations. Annotation copyright by Book News, Inc., Portland, OR







Analytical and Experimental Evaluation of the Supersonic Combustion Ramjet Engine. Volume Ii. Component Evaluation


Book Description

This was an experimental and analytical investigation to supply design information for the aerothermo design of a supersonic combustor for a flight test vehicle. The penetration of fuel jets into a supersonic stream was investigated in a cold flow supersonic wind tunnel and combustion test of scale model combustors were conducted in a Hypersonic Arc-Tunnel. Combustion tests of several configurations identified a burner having adequate performance characteristics for achieving the vehicle mission. The aerothermo design of the vehicle combustor was based on this tested configuration. This volume is devoted to investigations of Fuel Injection and Combustion in supersonic airstreams. (Author).