Experiment and numerical investigation of flow control on a supersonic inlet diffuser

Zhang, Jinsheng; Yuan, Hang; Wang, Yunfei; Huang, Guoping

doi:10.1016/j.ast.2020.106182

Cited by 28 publications

(9 citation statements)

References 11 publications

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“…The simulation for mixed external-internal flow field is a special case to the turbulence model determination. Zhang et al [35] studied the impacts of turbulence models on the numerical results. Both k-ε and Spalart-Allmaras turbulence models match well with experiment data of a 2D supersonic inlet, which contains external and internal flow field.…”

Section: Aerodynamic Characteristics Of the New Bump Inlet 41 Preparation Of Numerical Simulationmentioning

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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Section: Aerodynamic Characteristics Of the New Bump Inlet 41 Preparation Of Numerical Simulationmentioning

confidence: 99%

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

Zhang¹,

Huang²,

Musa³

2021

Aerospace

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“…There are other methods, such as the lip both translation and rotating variable-geometry inlet [19], the sidewall compression inlet adjustment with the lifting strut [20], a rigid structure rotation/translation scheme [21], and so on. Zhang [22] studied a two-dimensional variable-geometry inlet. The first stage of the inlet is curved compression, and the second compression wall extends to the throat and rotates around a fixed hinge.…”

Section: Introductionmentioning

confidence: 99%

Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment

et al. 2022

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According to the requirements of a wide speed range, a variable-geometry supersonic inlet with inner surface adjustment is studied. The basic design model of the inlet is established, and the influence of profile adjustment on the resisting back pressure ability and inlet performance boundary are analyzed using a theoretical method. Based on the numerical simulation method, the flow field simulation is carried out, and the flow field parameter distribution and performance of the adjustment inlet are studied in comparison with the fixed-geometry scheme. The results show that the starting Mach number is not changed for two inlet schemes because they have the same profile during low-speed flight. The fixed-geometry inlet has insufficient compression on the incoming flow, and the resisting back pressure ability decreases significantly during high-speed flight. The compression ratio and the compression wave system can be easily changed at the same time through the adjustment of the inner profile for the adjustable inlet during high-speed flight. Both the theoretical analysis and numerical simulation show that the resisting back pressure ability and performance are significantly improved after the adjustment. As such, the adjustment method in this paper can fundamentally solve the problem of the insufficient compression of the wide-range working inlet during high-speed flight, and the method can be easily realized.

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“…A number of studies have been carried out in the literature to provide an understanding of the effects of various internal geometric concepts (for supersonic diffuser, throat and subsonic diffuser) [1,2,[11][12][13], upstream flow conditions [13,14], unstart [12,14], buzz oscillations [6][7][8] as well as the various active and passive boundary-layer control methods [14][15][16][17][18][19] on intake performance. According to these studies, out of the various boundarylayer control methods, the active control using a bleed system is the most preferred method for practical usage because of its strong impact on performance improvement.…”

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confidence: 99%

“…According to these studies, out of the various boundarylayer control methods, the active control using a bleed system is the most preferred method for practical usage because of its strong impact on performance improvement. Several investigations, considering different types of intakes such as rectangular, axisymmetric, chin as well as wavecatcher/three-dimensional (3D) intakes [12][13][14][15][16][17][18] have shown that use of bleed and bypass systems lead to, i) an improvement in pressure recovery and flow uniformity because of the decrease in flow separation and the losses across the SWBLIs, ii) a delay in buzz oscillations because of shock stabilization [8,12] as well as iii) alleviate the "unstart because of SWBLI" [19][20][21]. It should be noted that, though the bleed systems result in an improvement in performance, they add to a loss in captured mass flow leading to drag penalty and the associated ducting leads to weight penalty.…”

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confidence: 99%

“…In addition to the bleed sizing, the choice of its location is also important to achieve optimum performance in the complete operating regime. Different studies have applied the bleed system in the neighborhood of the throat on the ramp/centerbody [16][17][18][19][20] and cowl [23], sidewalls [5,23] as well as the subsonic diffuser [15]; and found to have positive effects on the performance. Fisher [5] and Neale et al [23] have shown that in rectangular intakes the requirement of sidewall bleed systems can be avoided by placing the bleed at the throat.…”

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