Effects of Intake Modification on a Ramjet Engine

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The effects of intake modification on a Ramjet engine

A ramjet intake design analysis. Supersonic and hypersonic flights often make use of a ramjet engine during the cruise phase of the flight. The design of the intake affects important variables of the ramjet engine, namely Mach number distribution, formation of shocks and pressure distribution. Analysis of a normal intake design provides lower than optimal pressure to the combustion chamber. A geometric dimension modification on the intake, i.e. lengthening of the nosecone significantly improves the resultant pressure in the combustion chamber. Flow speed or the Mach number in the combustion chamber is also reduced. Over lengthening the nosecone could require infeasible initial flow speed; very high Mach number.

Introduction

The Ramjet engine is of significant importance due to the role that it played in the past and its potential in the future. In the past, it has been mostly used in missiles, Zaehringer & Whitfield (2004) with some applications in aircraft technology, Brossier et al. (1994). Its simplicity, having no moving parts, makes it a very attractive topic to be studied upon. Essentially, a typical ramjet engine can be divided into sections of inlet, burner and nozzle. The engine uses its high speed to compress the air which flows through the intake; the ramming effect. The ram air is then used to burn a fuel, Zaehringer & Whitfield (2004). The exhaust from the combustion then passes through a nozzle which accelerates the flow. Since the exit velocity is greater than the free stream velocity, thrust is produced Benson, (2006)

The major limiting factor is the speed requirement for the functioning of the ramjet. The ramjet will only provide thrust at speeds a...

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