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An Investigation into the Performance Characteristics of a Solid Fuel SCRAMJET Propulsion Device

W. J. Angus

Open publisher page 31 citations

Abstract

An investigation was conducted to evaluate the performance qualities of a supersonic ramjet propulsion device (SCRAMJET) using a solid fuel. The fuel grains were fabricated from Plexiglas and were cylindrical, with an axisymmetric, circular perforation that diverged in the downstream direction. A small amount of hydrogen gas was required in an initial recirculation zone in order to sustain combustion. With combustor inlet conditions of 150 psia, 1000(o)R, and a Mach number of 1.5, a combustor exit Mach number of 1.4 was maintained. Due to poor mixing conditions, the combustion efficiency of the solid fuel was only 57%.

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What this paper is about

An investigation was conducted to evaluate the performance qualities of a supersonic ramjet propulsion device (SCRAMJET) using a solid fuel. The fuel grains were fabricated from Plexiglas and were cylindrical, with an axisymmetric, circular perforation that diverged in the downstream direction. A small amount of hydrogen gas was required in an initial recirculation zone in order to sustain combustion. With combustor inlet conditions of 150 psia, 1000(o)R, and a Mach number of 1.5, a combustor exit Mach number of 1.4 was maintained. Due to poor mixing conditions, the combustion efficiency of the solid fuel was only 57%.

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Available abstract

An investigation was conducted to evaluate the performance qualities of a supersonic ramjet propulsion device (SCRAMJET) using a solid fuel. The fuel grains were fabricated from Plexiglas and were cylindrical, with an axisymmetric, circular perforation that diverged in the downstream direction. A small amount of hydrogen gas was required in an initial recirculation zone in order to sustain combustion. With combustor inlet conditions of 150 psia, 1000(o)R, and a Mach number of 1.5, a combustor exit Mach number of 1.4 was maintained. Due to poor mixing conditions, the combustion efficiency of the solid fuel was only 57%.

Key concepts: Scramjet, Combustor, Ramjet, Mach number, Supersonic speed, Combustion, Propulsion, Aerospace engineering

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