Supersonic inlet duct unstart induced by fuel jet injection

Hyungrok Do; Seong Kyun Im; M. Godfrey Mungal; Mark A. Cappelli

Supersonic inlet duct unstart induced by fuel jet injection

Hyungrok Do, Seong Kyun Im, M. Godfrey Mungal, Mark A. Cappelli

Research output: Contribution to conference › Paper › peer-review

Abstract

A high pressure transverse air jet is injected into a Mach 5 supersonic model inlet to induce inlet unstart. Planar laser Rayleigh scattering from condensed CO2 particles is used to visualize flow dynamics during the unstart process, while in some cases, wall pressure traces are simultaneously recorded. Boundary layer separation triggered by downstream surface pressure rise is found to precede the formation of a shock system, instantly followed by inlet unstart. Studies conducted over a range of initial inlet flow conditions reveal that the presence of turbulent wall boundary layers affects the unstart dynamics. It is found that relatively thick turbulent boundary layers facilitate faster inlet unstart, when compared to thin, laminar boundary layers.

Original language	English
Publication status	Published - 2011
Externally published	Yes
Event	7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011 - Ottawa, Canada Duration: 2011 Jul 28 → 2011 Jul 31

Conference

Conference	7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011
Country/Territory	Canada
City	Ottawa
Period	11/7/28 → 11/7/31

ASJC Scopus subject areas

Fluid Flow and Transfer Processes

Cite this

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title = "Supersonic inlet duct unstart induced by fuel jet injection",

abstract = "A high pressure transverse air jet is injected into a Mach 5 supersonic model inlet to induce inlet unstart. Planar laser Rayleigh scattering from condensed CO2 particles is used to visualize flow dynamics during the unstart process, while in some cases, wall pressure traces are simultaneously recorded. Boundary layer separation triggered by downstream surface pressure rise is found to precede the formation of a shock system, instantly followed by inlet unstart. Studies conducted over a range of initial inlet flow conditions reveal that the presence of turbulent wall boundary layers affects the unstart dynamics. It is found that relatively thick turbulent boundary layers facilitate faster inlet unstart, when compared to thin, laminar boundary layers.",

author = "Hyungrok Do and Im, {Seong Kyun} and Mungal, {M. Godfrey} and Cappelli, {Mark A.}",

year = "2011",

language = "English",

note = "7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011 ; Conference date: 28-07-2011 Through 31-07-2011",

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TY - CONF

T1 - Supersonic inlet duct unstart induced by fuel jet injection

AU - Do, Hyungrok

AU - Im, Seong Kyun

AU - Mungal, M. Godfrey

AU - Cappelli, Mark A.

PY - 2011

Y1 - 2011

N2 - A high pressure transverse air jet is injected into a Mach 5 supersonic model inlet to induce inlet unstart. Planar laser Rayleigh scattering from condensed CO2 particles is used to visualize flow dynamics during the unstart process, while in some cases, wall pressure traces are simultaneously recorded. Boundary layer separation triggered by downstream surface pressure rise is found to precede the formation of a shock system, instantly followed by inlet unstart. Studies conducted over a range of initial inlet flow conditions reveal that the presence of turbulent wall boundary layers affects the unstart dynamics. It is found that relatively thick turbulent boundary layers facilitate faster inlet unstart, when compared to thin, laminar boundary layers.

AB - A high pressure transverse air jet is injected into a Mach 5 supersonic model inlet to induce inlet unstart. Planar laser Rayleigh scattering from condensed CO2 particles is used to visualize flow dynamics during the unstart process, while in some cases, wall pressure traces are simultaneously recorded. Boundary layer separation triggered by downstream surface pressure rise is found to precede the formation of a shock system, instantly followed by inlet unstart. Studies conducted over a range of initial inlet flow conditions reveal that the presence of turbulent wall boundary layers affects the unstart dynamics. It is found that relatively thick turbulent boundary layers facilitate faster inlet unstart, when compared to thin, laminar boundary layers.

UR - http://www.scopus.com/inward/record.url?scp=85048537072&partnerID=8YFLogxK

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M3 - Paper

AN - SCOPUS:85048537072

T2 - 7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011

Y2 - 28 July 2011 through 31 July 2011

ER -

Supersonic inlet duct unstart induced by fuel jet injection

Abstract

Conference

ASJC Scopus subject areas

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