Investigation of supersonic flow about strut/endwall intersections in an annular duct

Williams, K. E.; Harloff, G. J.; Gessner, F. B.

doi:10.2514/3.12619

Cited by 9 publications

(3 citation statements)

References 26 publications

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“…Williams et al [92,91,90,93] performed several numerical and experimental studies about the interference produced by struts in an annular duct in supersonic flow. Those analyses serve as applications to engine development.…”

Section: Supersonic Flowmentioning

confidence: 99%

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Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

Tetrault

2000

38th Aerospace Sciences Meeting and Exhibit

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In transonic flow, the aerodynamic interference that occurs on a strut-braced wing airplane, pylons, and other applications is significant. The purpose of this work is to provide relationships to estimate the interference drag of wing-strut, wing-pylon, and wing-body ar- his office, leaving with more answers than questions. I also appreciate the fact that he has always had a friendly attitude towards me. I have enjoyed interacting with Dr. Kapania, whose cheerful attitude and perpective on life and research is very similar to mine. I would like to acknowledge the contribution of Dr. Grossman to the team in the field of numerical calculations and his desire of improving the life of the graduate students by forming the Graduate Advisory Committee. Dr. Raj deserves a lot of thanks for providing me with useful advice throughout this project despite his busy schedule. I appreciate the fact that he has always been interested in knowing more about the evolution of my research work and career. The "virtual" presence of Dr. Haftka during our weekly meetings has been very beneficial because of his ability to foresee difficulties and to get the team members to not lose sight of the big picture.

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Section: Supersonic Flowmentioning

confidence: 99%

“…In Ref. [92], the configuration contained four struts located circumferentially in an annular duct. Measurements were compared with CFD calculations performed on structured grids with a Reynolds-averaged Navier-Stokes flow solver.…”

Section: Supersonic Flowmentioning

confidence: 99%

Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

Tetrault

2000

38th Aerospace Sciences Meeting and Exhibit

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“…The combustion chamber of a continuous rotating detonation engine is usually of annular cavity structure, where fuel and oxidizer are injected through slots or round holes on the intake wall [9][10][11][12]. One or more detonation waves propagate and rotate along the circumferential direction at the head of the combustion chamber [13].…”

Section: Figure 1: Scramjet Engine Schematic Diagrammentioning

confidence: 99%

Research on the Combustion Mode and Thrust Performance of Rotating Detonation Scrarmjet Engines

2024

Eng OA

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Decades of research in hypersonic science and engineering have shown that scramjet engines are the preferred choice for powering hypersonic vehicles. In these engines, oblique shock combustion and rotating detonation combustion are two common combustion modes. This article primarily focuses on the numerical simulation and theoretical analysis of these two combustion modes. The research indicates that as the combustible mixture injected into the combustion chamber increases, the combustion mode transitions from deflagration combustion to self-sustaining detonation combustion and then to forced detonation combustion to maintain stable combustion in the chamber. Under self-sustaining detonation combustion mode, as the amount of combustible mixture injected into the chamber increases, the number of detonation waves gradually increases from one to multiple and the angle between the detonation waves and the inflow changes from acute to right angles. In the forced detonation combustion mode, the minimum shock wave intensity required to initiate detonation combustion can be obtained by drawing a tangent from the Rayleigh line. The structure generating oblique shock waves in the combustion chamber needs to match the shock wave intensity. In the detonation combustion mode, both the exit total temperature and specific impulse of the combustion chamber increase with the increase in Mach number at the inlet, while the pressure ratio decreases. This article provides a reference for the design of the combustion chamber in supersonic combustion ramjet engines.

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Flowfield characteristics of struts in supersonic annular flow

Williams

Gessner

1996

Engineering Turbulence Modelling and Experiments

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Investigation of supersonic flow about strut/endwall intersections in an annular duct

Cited by 9 publications

References 26 publications

Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

Research on the Combustion Mode and Thrust Performance of Rotating Detonation Scrarmjet Engines

Flowfield characteristics of struts in supersonic annular flow

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