The influence of boundary layers on supersonic inlet flow unstart induced by mass injection

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

Research output: Contribution to journalArticle

46 Citations (Scopus)

Abstract

A transverse jet is injected into a supersonic model inlet flow to induce 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. Studies conducted over a range of inlet configurations reveal that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers in asymmetric wall boundary layer conditions prompt the formation of unstart shocks; in symmetric boundary conditions lead to the propagation of pseudo-shocks; and in both cases facilitate fast inlet unstart, when compared with thin, laminar boundary layers. Incident shockwaves and associated reflections are found to affect the speed of pressure disturbances. These disturbances, which induce boundary layer separation, are found to precede the formation of unstart shocks. The results confirm the importance of and need to better understand shock-boundary layer interactions in inlet unstart dynamics.

Original languageEnglish
Pages (from-to)679-691
Number of pages13
JournalExperiments in Fluids
Volume51
Issue number3
DOIs
Publication statusPublished - 2011 Sep 1
Externally publishedYes

Fingerprint

supersonic inlets
Inlet flow
boundary layers
Boundary layers
shock
injection
disturbances
inlet flow
boundary layer separation
wall pressure
laminar boundary layer
turbulent boundary layer
Rayleigh scattering
Laminar boundary layer
boundary conditions
propagation
Boundary conditions
configurations
Lasers
lasers

ASJC Scopus subject areas

  • Computational Mechanics
  • Mechanics of Materials
  • Physics and Astronomy(all)
  • Fluid Flow and Transfer Processes

Cite this

The influence of boundary layers on supersonic inlet flow unstart induced by mass injection. / Do, Hyungrok; Im, Seong Kyun; Mungal, M. Godfrey; Cappelli, Mark A.

In: Experiments in Fluids, Vol. 51, No. 3, 01.09.2011, p. 679-691.

Research output: Contribution to journalArticle

Do, Hyungrok ; Im, Seong Kyun ; Mungal, M. Godfrey ; Cappelli, Mark A. / The influence of boundary layers on supersonic inlet flow unstart induced by mass injection. In: Experiments in Fluids. 2011 ; Vol. 51, No. 3. pp. 679-691.
@article{b83c70cd68b74961a28baaa0e3847e2a,
title = "The influence of boundary layers on supersonic inlet flow unstart induced by mass injection",
abstract = "A transverse jet is injected into a supersonic model inlet flow to induce 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. Studies conducted over a range of inlet configurations reveal that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers in asymmetric wall boundary layer conditions prompt the formation of unstart shocks; in symmetric boundary conditions lead to the propagation of pseudo-shocks; and in both cases facilitate fast inlet unstart, when compared with thin, laminar boundary layers. Incident shockwaves and associated reflections are found to affect the speed of pressure disturbances. These disturbances, which induce boundary layer separation, are found to precede the formation of unstart shocks. The results confirm the importance of and need to better understand shock-boundary layer interactions in inlet unstart dynamics.",
author = "Hyungrok Do and Im, {Seong Kyun} and Mungal, {M. Godfrey} and Cappelli, {Mark A.}",
year = "2011",
month = "9",
day = "1",
doi = "10.1007/s00348-011-1077-3",
language = "English",
volume = "51",
pages = "679--691",
journal = "Experiments in Fluids",
issn = "0723-4864",
publisher = "Springer Verlag",
number = "3",

}

TY - JOUR

T1 - The influence of boundary layers on supersonic inlet flow unstart induced by mass injection

AU - Do, Hyungrok

AU - Im, Seong Kyun

AU - Mungal, M. Godfrey

AU - Cappelli, Mark A.

PY - 2011/9/1

Y1 - 2011/9/1

N2 - A transverse jet is injected into a supersonic model inlet flow to induce 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. Studies conducted over a range of inlet configurations reveal that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers in asymmetric wall boundary layer conditions prompt the formation of unstart shocks; in symmetric boundary conditions lead to the propagation of pseudo-shocks; and in both cases facilitate fast inlet unstart, when compared with thin, laminar boundary layers. Incident shockwaves and associated reflections are found to affect the speed of pressure disturbances. These disturbances, which induce boundary layer separation, are found to precede the formation of unstart shocks. The results confirm the importance of and need to better understand shock-boundary layer interactions in inlet unstart dynamics.

AB - A transverse jet is injected into a supersonic model inlet flow to induce 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. Studies conducted over a range of inlet configurations reveal that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers in asymmetric wall boundary layer conditions prompt the formation of unstart shocks; in symmetric boundary conditions lead to the propagation of pseudo-shocks; and in both cases facilitate fast inlet unstart, when compared with thin, laminar boundary layers. Incident shockwaves and associated reflections are found to affect the speed of pressure disturbances. These disturbances, which induce boundary layer separation, are found to precede the formation of unstart shocks. The results confirm the importance of and need to better understand shock-boundary layer interactions in inlet unstart dynamics.

UR - http://www.scopus.com/inward/record.url?scp=80052677309&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=80052677309&partnerID=8YFLogxK

U2 - 10.1007/s00348-011-1077-3

DO - 10.1007/s00348-011-1077-3

M3 - Article

VL - 51

SP - 679

EP - 691

JO - Experiments in Fluids

JF - Experiments in Fluids

SN - 0723-4864

IS - 3

ER -