Design and Test of a Hypersonic Isentropic-Spike Intake with Aligned Cowl

Matthews, Alexander; Jones, T. V.; Cain, T. M.

doi:10.2514/1.13000

Cited by 11 publications

(2 citation statements)

References 3 publications

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“…It was first proposed by Curran and Craig [ 10 ] and has since become the standard technique recommended by the scramjet textbook [ 11 – 13 ]. A practical example of this method can be found in Matthews et al [ 14 ] and Matthews and Jones [ 15 ]. The concept relies on the conservation of mass, momentum and energy of the captured airstream of flow entering the inlet.…”

Section: Introductionmentioning

confidence: 99%

Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator

Idris

Saad

Zare‐Behtash

et al. 2014

Sensors

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Scramjets have become a main focus of study for many researchers, due to their application as propulsive devices in hypersonic flight. This entails a detailed understanding of the fluid mechanics involved to be able to design and operate these engines with maximum efficiency even at their off-design conditions. It is the objective of the present cold-flow investigation to study and analyse experimentally the mechanics of the fluid structures encountered within a generic scramjet inlet at M = 5. Traditionally, researchers have to rely on stream-thrust analysis, which requires the complex setup of a mass flow meter, a force balance and a heat transducer in order to measure inlet-isolator performance. Alternatively, the pitot rake could be positioned at inlet-isolator exit plane, but this method is intrusive to the flow, and the number of pitot tubes is limited by the model size constraint. Thus, this urgent need for a better flow diagnostics method is addressed in this paper. Pressure-sensitive paint (PSP) has been applied to investigate the flow characteristics on the compression ramp, isolator surface and isolator sidewall. Numerous shock-shock interactions, corner and shoulder separation regions, as well as shock trains were captured by the luminescent system. The performance of the scramjet inlet-isolator has been shown to improve when operated in a modest angle of attack.

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Section: Introductionmentioning

confidence: 99%

Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator

Idris

Saad

Zare‐Behtash

et al. 2014

Sensors

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“…RANS methods with a Spalart-Allmaras turbulence model can adequately model the flowfield in a hypersonic intake and can adequately resolve the presence of interference phenomena such as separation. This was supported by Babinsky (2011), Moerel (2009) and Matthews (2005). The strength of the bow shock over the increasing cowl lip radii was observed to be stronger than the interfering oblique shock emanating from the centerbody tip.…”

Section: Discussionmentioning

confidence: 65%

RANS Modelling of Shock-Wave Boundary Layer Interaction in a Mixed Compression Axisymmetric Hypersonic Intake

Kumar

Thornber

2016

AMM

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This work focuses on developing a design methodology for a mixed compression axisymmetric hypersonic intake and numerically computing flow around the designed intake using RANS methods to study shock/shock and shock wave/boundary layer interaction. The focus of the computational study is on the effect of increasing the blunt radius of the cowl lip on the resulting shock/shock interaction between the oblique shock emanating from the cone compression apex and the bow shock on the cowl lip; as well the resulting reflected oblique shock boundary layer interaction from the cowl tip onto the cone compression surface. Three (3) radii are tested: 2mm, 16mm and 32mm at Mach 2 and the study is extended to a nominal 16mm condition at Mach 5. It is found that with increasing cowl-lip radius the magnitude of the shock-wave/boundary layer interaction increases significantly. Separation on the cone compression surface is observed at the 16mm and 32mm case at the Mach 2 position and in the 16mm case at the Mach 5 position. In addition in the 16mm and 32mm cases at the Mach 2 position, a Mach stem is observed. The shock/shock interactions, however, are found to be less dramatic. Type III and IV phenomena are observed, however, there is limited interference with the bow shock.

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Gun Tunnels

Buttsworth¹

2015

Experimental Methods of Shock Wave Research

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Design and Test of a Hypersonic Isentropic-Spike Intake with Aligned Cowl

Cited by 11 publications

References 3 publications

Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator

Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator

RANS Modelling of Shock-Wave Boundary Layer Interaction in a Mixed Compression Axisymmetric Hypersonic Intake

Gun Tunnels

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