Numerical investigation on the forced oscillation of shock train in hypersonic inlet with translating cowl

Wen, Sheng; Chang, Juntao; Zhang, Junlong; Jun-hai, MA; Wang, Ziao; Bao, Wen

doi:10.1016/j.ast.2019.02.022

Cited by 34 publications

(8 citation statements)

References 45 publications

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“…As the connection of the inlet and the combustor, a diffuser 30,31 is designed to contain the high pressure rise generated by heat release within the combustor to ensure the normal starting work of the inlet. The airflow compression in the diffuser is mainly performed by the shock train, which decelerates the flow before it enters the combustor.…”

Section: Numerical Simulation and Wind Tunnel Experimentsmentioning

confidence: 99%

Experimental and numerical investigation of a supersonic inlet with double S-bend diffuser

Zhang

Yuan

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Design of a supersonic inlet with double S-bend diffuser was developed. Numerical simulation and wind tunnel experiment were carried out to investigate the aerodynamic performance and variable geometric rules of the inlet. The result indicates that the variable geometry scheme adopted solves the contradiction between starting performance at low Mach number and aerodynamic performance at high Mach number. The inlet works normally and stably over a wide speed range. At design point, the total pressure recovery coefficient reaches 0.47. In addition, two different kinds of inlets with double S-bend diffuser and single S-bend diffuser were studied. Compared with the double S-bend diffuser, the total pressure recovery coefficient of the single S-bend diffuser is higher at low Mach number (Ma0 < 3) and lower at high Mach number (Ma0 > 3). With the increase of backpressure, shock train mainly moves upstream along the low-energy flow region in the diffuser. For the double S-bend diffuser, shock train will first move along the lower corner and then along the upper corner. For the single S-bend diffuser, it will only move along the upper corner. The strong secondary flow of the double S-bend is the main reason for the above phenomenon.

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Section: Numerical Simulation and Wind Tunnel Experimentsmentioning

confidence: 99%

Experimental and numerical investigation of a supersonic inlet with double S-bend diffuser

Zhang

Yuan

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Vanstone et al [11,12] proposed a simple physics-based model for the prediction of shock-train location. Shi et al [13] compared the shock train behavior under sinusoidal and constant backpressure and they found that the oscillations in shock train move downstream of the flow. The incident shocks effects on close-loop control (CLC) of the shock train location are experimentally studied by Li et al [14] who found that it makes the CLC unstable.…”

Section: Introductionmentioning

confidence: 99%

Large eddy simulation of pseudo shock structure in a convergent–long divergent duct

Mousavi

Kamali

Sotoudeh

et al. 2021

Computers & Mathematics with Applications

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In this paper, the Pseudo shock structure in a convergent-long divergent duct is investigated using large eddy simulation on the basis of Smagorinsky-Lilly, Wall-Adapting Local Eddy-Viscosity and Algebraic Wall-Modeled LES subgrid models. The first objective of the study is to apply different subgrid models to predict the structure of Lambda form shocks system, while the ultimate aim is to obtain further control of the shock behavior. To achieve these goals, the dynamic grid adaption and hybrid initialization techniques are applied under the 3D investigation to reduce numerical errors and computational costs. The results are compared to the existing experimental data and it is found that the WMLES subgrid model results in more accurate predictions when compared to the other subgrid models. Subsequently, the influences of the divergent section length with the constant ratio of the outlet to throat area and, the effects of discontinuity of the wall temperature on the flow physics are investigated. The results indicate that the structure of compressible flow in the duct is affected by varying these parameters. This is then further discussed to provide a deeper physical understanding of the mechanism of Pseudo shock motion.

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“…The direct cause of inlet unstart is that the swallowed inflow exceeds the flow capacity of the throat. Except for the backpressure fluctuation from the combustor [9][10][11], the internal contraction ratio (ICR) is the key parameter to determine the inlet start. Kantrowitz [12] first proposed the inviscid ICR calculating equation based on 1D steady flow assumption.…”

Section: Introductionmentioning

confidence: 99%

Spillage-Adaptive Fixed-Geometry Bump Inlet of Wide Speed Range

Zhang¹,

Huang²,

Musa³

2021

Aerospace

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In this work, a new spillage-adaptive bump inlet concept is proposed to widen the speed range for hypersonic air-breathing flight vehicles. Various approaches to improve the inlet start-ability are summarized and compared, among which the bump-inlet pattern holds the merits of high lift-to-drag ratio, boundary layer diversion, and flexible integration ability. The proposed spillage-adaptive concept ensures the inlet starting performance by spilling extra mass flow away at low speed number conditions. The inlet presetting position is determined by synthetically evaluating the flow uniformity and the low-kinetic-energy fluid proportion. The numerical results show that the flow spillage of the inlet increases with the inflow speed decrease, which makes the inlet easier to start at low speed conditions (M 2.5–6.0). The effects of the boundary layer on spillage are also studied in this work. The new integration pattern releases the flow spillage potentials of three-dimensional inward-turning inlets by reasonably arranging the inlet compression on the bump surface. Future work will focus on the spillage-controllable design method.

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Numerical investigation on the forced oscillation of shock train in hypersonic inlet with translating cowl

Cited by 34 publications

References 45 publications

Experimental and numerical investigation of a supersonic inlet with double S-bend diffuser

Experimental and numerical investigation of a supersonic inlet with double S-bend diffuser

Large eddy simulation of pseudo shock structure in a convergent–long divergent duct

Spillage-Adaptive Fixed-Geometry Bump Inlet of Wide Speed Range

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