Flow Characteristics of Small-Sized Supersonic Inlets

Lee, Hyoung Jin; Lee, Bok Jik; Kim, Sung Don; Jeung, In‐Seuck

doi:10.2514/1.46101

Cited by 47 publications

(17 citation statements)

References 17 publications

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“…This change is caused by the slightly inclined vertical branches of characteristic lines for using software to simulate. In addition, the stability margin can be defined by equation (8). The history of stability margin is plotted in Figure 7(d).…”

Section: Simulation For Start Modementioning

confidence: 99%

Mathematical modeling and characteristic analysis of scramjet buzz

Chang

Wang

Bao

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Buzz is an important issue for a scramjet engine. A mathematical model of buzz oscillations is necessary for control system design. Control-oriented models of hypersonic vehicle propulsion systems require a reduced-order model that is accurate to some extent but requires less than a few seconds of computational time. To achieve this goal, a reducedorder model of buzz oscillations for a scramjet engine is built by introducing the modeling idea of Moore-Greitzed model for compressors. The introduction of characteristic lines avoids the complex interactions in hypersonic inlet, such as shock-shock interactions and shock-boundary layer interaction. And the inlet characteristics are obtained from the pressure signal of combustor. Based on the established buzz model, we can predict the inlet performance, characterize the stability margin of inlet, reflect the oscillatory characteristics of inlet buzz including the dominant amplitude and frequency and describe the transition process of inlet buzz.

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Section: Simulation For Start Modementioning

confidence: 99%

Mathematical modeling and characteristic analysis of scramjet buzz

Chang

Wang

Bao

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Since the inlet buzz was first observed by Oswatitsch [7] in the experimental study of an asymmetrically configured missile inlet system, numerous remarkable experimental investigations have been carried out in the past decades. Thus, numerous cognitions concerning the mechanism of the inlet buzz have been obtained: (1) In a general sense, the inlet buzz could be classified into two types, namely the little buzz and the big buzz [3,4,[8][9][10][11][12]. The former one is basically characterized by the flow 2 of 23 oscillation with a small amplitude, while the latter features large-scale shock motion accompanied by enormous pressure oscillation and flow choke.…”

Section: Introductionmentioning

confidence: 99%

Spatiotemporal Characterization and Suppression Mechanism of Supersonic Inlet Buzz with Proper Orthogonal Decomposition Method

Luo

Wei

et al. 2020

Energies

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The buzz phenomenon of a typical supersonic inlet is analyzed using the unsteady Reynolds Average Navier-Stokes (RANS) simulation and proper orthogonal decomposition (POD) method. The dominant flow patterns and characteristics of the buzzed flow are obtained by decoupling the computed pressure field into spatial and temporal sub-parts based on the POD method. The supersonic inlet buzz phenomenon could be approximated as a product of decoupled temporal and spatial terms, and the one-dimensional (1D) mathematical model is therefore proposed. The standard deviations of the unsteady pressure fields from both the numerical simulation and the model prediction are compared. The limited discrepancy can be observed, and the good agreement validates the credibility of the proposed 1D model. The numerical simulation and the 1D model prediction are presented to explore the unsteady-jet control with a small perturbation. The results of the 1D model and the numerical simulation achieve good agreements with each other in terms of the overall trend. Finally, POD modal energy is employed to analyze the buzz suppression mechanism. When the jet frequency is identical to the dominant frequency of the buzz and the jet phase is opposite to the oscillation phase of the captured mass flow, the buzz suppression could be more efficient. The buzz suppression mechanism could be explained in two aspects. For one thing, the complex flow structure is suppressed and the first average modal energy in the inlet is increased. For another, the energy redistribution among each POD mode is achieved and the flow stability is gradually enhanced.

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“…Furthermore, the struts in the designed engine will also rotate at the same speed with the whole engine. In the non-spinning motion, the struts are usually neglected for simplicity because of their relatively insignificant effects to the flow [96]. However, when the spinning rate is high (i.e.…”

Section: Discussion About the Combustor Inflow Conditions In Spinningmentioning

confidence: 99%

Numerical study of trapped vortex combustors characteristics in small ramjets

Chen¹

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my current supervisor, who continuously provides me valuable suggestions and discussions during these years in many ways. I am also grateful to Dr. Simon Ching-Man Yu of Singapore Institute of Technology, my co-supervisor, for continuously providing me encouragement, guidance, discussions and caring in both research and personal life. Without their guidance, the research would not have been so enriching and fulfilling.

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Flow Characteristics of Small-Sized Supersonic Inlets

Cited by 47 publications

References 17 publications

Mathematical modeling and characteristic analysis of scramjet buzz

Mathematical modeling and characteristic analysis of scramjet buzz

Spatiotemporal Characterization and Suppression Mechanism of Supersonic Inlet Buzz with Proper Orthogonal Decomposition Method

Numerical study of trapped vortex combustors characteristics in small ramjets

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