Studies of scramjet/airframe integration                                                   techniques for hypersonic aircraft

Edwards, C. L. W.; Small, William; Weidner, J. P.; Johnston, Patrick

doi:10.2514/6.1975-58

“…The actual advantage that may be realized can be determined only by detailed investigations of the aerodynamic, cooling and propUlsion problems which are unique to this Mach number range and by rather sophisticated studies of integration between the aerodynamic configuration, the propulsion system and the thermal control of the structure. The configuration and integration analyses which appear in Kirkham & Hunt (1977), Edwards, Small & Weidner (1975), Small, Weidner & Johnston (1974) and Nowak & Kelley (1976) provide substantial insight into both the importance and the formidable difficulty of the problem.…”

Section: Inl'roductionmentioning

confidence: 99%

Progress toward shock enhancement of supersonic combustion processes

Marble

¹

,

HENDRICKES

²

,

Zukoski

³

1987

23rd Joint Propulsion Conference

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In air breathing propulsion systems for flight at Mach numbers 7 to 20, it is generally accepted that the combustion processes will be carried out at supersonic velocities with respect to the engine. The resulting brief residence time places a premium on rapid mixing of the fuel and air. To address this issue we &re investigating a mechanism for enhancing the rate of mixing between air and hydrogen fuel over rates that are expected in shear layers and jets.The mechanism rests upon the strong vorticity induced at the interface between a light and heavy gas by an intense pressure gradient. The specific phenomenon under investigation is the rapid mixing induced by interaction of a weak oblique shock with a cylindrical jet of hydrogen embedded in air. The status of our investigations is described in three parts: a) shock tube investigation of the distortion and mixing induced by shock waves impinging on cylindric of hydrogen embedded in air, b) the molecular mixing and chemical reaction in large vortices, periodically formed in a channel, and c) two-dimensional non-steady and three-dimensional steady numerical studies of shock interaction with cylindrical volumes of hydrogen in air.

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“…One of the most important design aspects of a hypersonic space plane is the propulsion/airframe integration. The advantages of such a design in providing increased efficiencies has been well established [1,2]. The shape of the forebody and aftbody play a prominent role.…”

Section: Chapter 1 Introductionmentioning

confidence: 99%

Computation of the integrated aerodynamic and propulsive flowfields of a generic hypersonic space plane

Wadawadigi

¹

0

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Progress Toward Shock Enhancement of Supersonic Combustion Processes

Marble

¹

,

Hendricks

²

,

Zukoski

³

1989

Lecture Notes in Engineering

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In air breathing propulsion systems for flight at Mach numbers 7 to 20, it is generally accepted that the combustion processes will be carried out at supersonic velocities with respect to the engine. The resulting brief residence time places a premium on rapid mixing of the fuel and air. To address this issue we &re investigating a mechanism for enhancing the rate of mixing between air and hydrogen fuel over rates that are expected in shear layers and jets.The mechanism rests upon the strong vorticity induced at the interface between a light and heavy gas by an intense pressure gradient. The specific phenomenon under investigation is the rapid mixing induced by interaction of a weak oblique shock with a cylindrical jet of hydrogen embedded in air. The status of our investigations is described in three parts: a) shock tube investigation of the distortion and mixing induced by shock waves impinging on cylindric of hydrogen embedded in air, b) the molecular mixing and chemical reaction in large vortices, periodically formed in a channel, and c) two-dimensional non-steady and three-dimensional steady numerical studies of shock interaction with cylindrical volumes of hydrogen in air.

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Studies of scramjet/airframe integration techniques for hypersonic aircraft

Cited by 20 publications

References 1 publication

Progress toward shock enhancement of supersonic combustion processes

Progress toward shock enhancement of supersonic combustion processes

Computation of the integrated aerodynamic and propulsive flowfields of a generic hypersonic space plane

Progress Toward Shock Enhancement of Supersonic Combustion Processes

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