Isolator Dynamics and Heat Release during Unstart of a Dual-Mode Scramjet

Riley, Logan P.; Hagenmaier, Mark A.; Donbar, Jeffrey M.; Gaitonde, Datta V.

doi:10.2514/6.2017-0554

Cited by 5 publications

(1 citation statement)

References 60 publications

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“…The severe limitations imposed by the supersonic combustion in hypersonic air-breathing propulsion systems motivates the extensive Computational Fluid Dynamics (CFD) and experimental investigations on the aero-thermal coupling between hypersonic inlets, isolator and combustor [1,2,3,4,5,6]. The CFD approach is somehow privileged and it is also used in designing the test facilities for the experimental investigations.…”

Section: Introductionmentioning

confidence: 99%

Optimal aerodynamic design of scramjet facility nozzles

Degregori¹,

Ferlauto²

2018

AIP Conference Proceedings

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An hybrid approach to optimization is applied to the aerodynamic design of a device that acts as a facility nozzle and inlet distortion generator for a direct-connect scramjet combustor test-rig. The solution of the design problem is sought by using different approaches of CFD analysis and optimization tools. The initial design is based on the solution of an inverse problem coupled to optimization by genetic algorithms. The result of the optimization is then tested by CFD simulations of the directconnect facility and the shock reflection patterns are compared toat of the in-flight configuration. The verification of nozzle design and the assessment of the prescribed flow distortion are then carried out by numerical simulations of the flowfield of the whole direct-connect facility by an URANS solver. The proposed procedure is checked by designing a facility nozzle and distortion generator system for a scramjet model available in the open literature.

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