Physical insight into a Mach 7.2 compression corner flow

Konstantinos Ritos; Ioannis W. Kokkinakis; Dimitris Drikakis

doi:10.2514/6.2018-1810

Physical insight into a Mach 7.2 compression corner flow

Konstantinos Ritos, Ioannis W. Kokkinakis, Dimitris Drikakis

Mechanical And Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

4 Citations (Scopus)

67 Downloads (Pure)

Abstract

High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Re_θ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.

Original language	English
Title of host publication	2018 AIAA Aerospace Sciences Meeting
Place of Publication	Reston, VA
DOIs	https://doi.org/10.2514/6.2018-1810
Publication status	Published - 8 Jan 2018
Event	AIAA SciTech 2018 - Gaylord Palms, Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018 https://scitech.aiaa.org/Register/

Conference

Conference	AIAA SciTech 2018
Country/Territory	United States
City	Kissimmee
Period	8/01/18 → 12/01/18
Internet address	https://scitech.aiaa.org/Register/

Keywords

large eddy simulations
shock-boundary layer interaction
grid-convergence stud
turbulent flow properties

Access to Document

10.2514/6.2018-1810

Ritos-etal-AIAA-2018-Physical-insight-into-a-Mach-7.2-compression-corner-flowAccepted author manuscript, 3.83 MB

Cite this

@inproceedings{d111e40143224ac99a0fb2ba7fc194c5,

title = "Physical insight into a Mach 7.2 compression corner flow",

abstract = "High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.",

keywords = "large eddy simulations, shock-boundary layer interaction, grid-convergence stud, turbulent flow properties",

author = "Konstantinos Ritos and Kokkinakis, {Ioannis W.} and Dimitris Drikakis",

year = "2018",

month = jan,

day = "8",

doi = "10.2514/6.2018-1810",

language = "English",

isbn = "9781624105241",

booktitle = "2018 AIAA Aerospace Sciences Meeting",

note = "AIAA SciTech 2018 ; Conference date: 08-01-2018 Through 12-01-2018",

url = "https://scitech.aiaa.org/Register/",

}

TY - GEN

T1 - Physical insight into a Mach 7.2 compression corner flow

AU - Ritos, Konstantinos

AU - Kokkinakis, Ioannis W.

AU - Drikakis, Dimitris

PY - 2018/1/8

Y1 - 2018/1/8

N2 - High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.

AB - High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.

KW - large eddy simulations

KW - shock-boundary layer interaction

KW - grid-convergence stud

KW - turbulent flow properties

UR - https://arc.aiaa.org/doi/book/10.2514/MASM18

U2 - 10.2514/6.2018-1810

DO - 10.2514/6.2018-1810

M3 - Conference contribution book

SN - 9781624105241

BT - 2018 AIAA Aerospace Sciences Meeting

CY - Reston, VA

T2 - AIAA SciTech 2018

Y2 - 8 January 2018 through 12 January 2018

ER -

Physical insight into a Mach 7.2 compression corner flow

Abstract

Conference

Keywords

Access to Document

Other files and links

Fingerprint

Shock-induced Turbulence and Acoustic Loading on Aerospace Structures

Cite this

Physical insight into a Mach 7.2 compression corner flow

Abstract

Conference

Keywords

Access to Document

Other files and links

Fingerprint

Projects

Shock-induced Turbulence and Acoustic Loading on Aerospace Structures

Cite this