Assessment of Cavity Covered with Porous Surface in Controlling Shock/Boundary-Layer Interactions in Hypersonic Intake

Jana, Tamal; T., Thillaikumar; Kaushik, Mrinal

doi:10.1007/s42405-020-00269-4

Cited by 7 publications

(2 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Since their effects on the boundary layer are non-linear, the investigation of their combined effects is essential for a complete understanding. Considering this in mind, Jana et al (2020) investigated the effect of a porous cavity in a mixed compression double ramp hypersonic intake (operating at Mach 5.7 and Mach 7.9 flow conditions) [118]. It is observed that the shallow cavity deployed over a porous surface can reduce the shock strength; the Fig.…”

Section: Plasma Jets (Active Control) [98-102]mentioning

confidence: 99%

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Jana

Kaushik

2022

Adv. Aerodyn.

Self Cite

View full text Add to dashboard Cite

The primary focus of the present survey is to categorize the results of various investigations on the Shock/Boundary-Layer Interactions (SBLIs), their repercussions, and the effective ways to control them. The interactions of shock waves with the boundary layer are an important area of research due to their ubiquity in several applications ranging from transonic to hypersonic flows. Therefore, there is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain accuracy. Considering this in mind, this article presents some key features of the physical nature of SBLIs, their consequences, and the control techniques in a sequential manner; in particular, the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail.

show abstract

Section: Plasma Jets (Active Control) [98-102]mentioning

confidence: 99%

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Jana

Kaushik

2022

Adv. Aerodyn.

Self Cite

View full text Add to dashboard Cite

show abstract

“…In a hypersonic inlet, large-scale separated flow is easily induced when intense lip shock compacts into the opposite boundary layer. The status of the inlet then becomes unstart, which is the most conventional unstart mode [13][14][15][16]. The oscillation of the unstart mode is stronger than that of the start mode, which is affected by factors including the boundary layer [17] and back pressure [18].…”

Section: Introductionmentioning

confidence: 99%

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

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

View full text Add to dashboard Cite

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.

show abstract

Numerical Investigation on Shock-Wave and Boundary-Layer Interactions Inside the Axisymmetric and Planar Scramjet Intakes with Different Cowl Orientations

Sharath,

Jana

2024

Lecture Notes in Mechanical Engineering

View full text Add to dashboard Cite

Assessment of Cavity Covered with Porous Surface in Controlling Shock/Boundary-Layer Interactions in Hypersonic Intake

Cited by 7 publications

References 15 publications

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

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

Numerical Investigation on Shock-Wave and Boundary-Layer Interactions Inside the Axisymmetric and Planar Scramjet Intakes with Different Cowl Orientations

Contact Info

Product

Resources

About