Feasibility of employing the restarting process to evaluate the self-starting ability for hypersonic inlets

Xie, Wen-zhong; Jin, Yi; Gao, Yan; Yang, Shu-Zi; Zeng, Cheng; Guo, Shengmin

doi:10.1016/j.ast.2020.106347

Cited by 17 publications

(2 citation statements)

References 20 publications

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“…Because decreasing the angle of attack (alpha) increases the Mach number in front of the inlet, self-start can also be achieved through this process [25,26]. Furthermore, if unstart is caused by excessive back pressure [27,28] and other factors allow the inlet to self-start, self-start can be achieved after the back pressure is released [29,30].…”

Section: Introductionmentioning

confidence: 99%

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

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Intense shock boundary-layer interaction may lead to multiple unstart modes existing in a hypersonic inlet. Thus, self-start problems become complex and cannot be explained using the classical double-solution theory of air inlet. The essence of the self-start process of a hypersonic inlet is the vanishment of separations near or in the inlet. To clarify self-start characteristics, experiments were conducted on three distinct types of unstart mode: the flow mode of small separation on body (SSB), large separation on body (LSB), and dual separations on both body and lip (DSBL); researchers recently discovered these as the unstart modes of hypersonic inlet. The results from the current experiment are as follows: (1) The SSB vanishes by raising the angle of attack (alpha). Before the vanishing point is reached, there is a dwindling process for this separation. (2) The LSB vanishes through acceleration or a decreasing alpha. (3) DSBL are difficult to vanish directly, which results in poor self-start performance. However, the DSBL flow mode may convert to LSB unstart form—which is easier to self-start—by decreasing the alpha. The Flow Field Reconstruction Method was designed to improve the self-start of the DSBL flow mode, and it was validated through experiments. Analysis of the flow mechanism revealed the reason for the poor self-start performance of the DSBL unstart mode: large-scale separation on the lip side cannot be promoted to vanish through broadwise spillage due to the resistance of sideboards. The results of this study could greatly enrich the existing theory of start problems for hypersonic inlets.

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Section: Introductionmentioning

confidence: 99%

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

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“…The corresponding ICR limit is obtained when the ending shock is located at the entrance, and M throat approaches 1.0. Xie [13,14] developed a threelayer model to predict the ICR limit at viscous conditions. The improvement of inlet start performance is carried out in two directions: one is to decrease the internal compression ratio and the other is to remove the boundary layer.…”

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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Suppression of flow response hysteresis in the throttling/unthrottling process for supersonic inlet

Jin

Zhang

et al. 2023

Acta Astronautica

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Feasibility of employing the restarting process to evaluate the self-starting ability for hypersonic inlets

Cited by 17 publications

References 20 publications

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

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

Suppression of flow response hysteresis in the throttling/unthrottling process for supersonic inlet

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