Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets

Hideaki Ogawa, H. Babinsky

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Citations (Scopus)

Abstract

The effects of three dimensional bump control on separated shock-wave / boundarylayer interactions have been investigated experimentally at M = 1.5, aiming to reduce total pressure losses incurred by strong normal shock / boundary-layer interactions. Such a situation occurs, for example, inside mixed-compression supersonic engine inlets or on external-compression inlets. Various bump configurations have been tested and their effects have been evaluated in various aspects such as total pressure recovery and boundary-layer thickness. Without control, the normal shock caused a region of relatively two-dimensional separation. Three-dimensional bumps commonly broke up this separation into individual regions of attached and separated flow, giving an overall reduction of the magnitude of separation. Fairly two-dimensional λ-shock structures and streamwise vortex pairs have been observed in all tested configurations. A configuration comprising multiple long, high, narrow rounded bumps has demonstrated the best performance, producing an appreciable total pressure saving as much as 30% owing to a λ-shock benefit with minimum viscous penalty from localised separation.

Original languageEnglish
Title of host publication46th AIAA Aerospace Sciences Meeting and Exhibit
Publication statusPublished - Dec 1 2008
Event46th AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 7 2008Jan 10 2008

Publication series

Name46th AIAA Aerospace Sciences Meeting and Exhibit

Other

Other46th AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/7/081/10/08

Fingerprint

Boundary layers
Engines
Shock waves
Vortex flow
Recovery

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Ogawa, H., & Babinsky, H. (2008). Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets. In 46th AIAA Aerospace Sciences Meeting and Exhibit [2008-0599] (46th AIAA Aerospace Sciences Meeting and Exhibit).

Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets. / Ogawa, Hideaki; Babinsky, H.

46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. 2008-0599 (46th AIAA Aerospace Sciences Meeting and Exhibit).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ogawa, H & Babinsky, H 2008, Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets. in 46th AIAA Aerospace Sciences Meeting and Exhibit., 2008-0599, 46th AIAA Aerospace Sciences Meeting and Exhibit, 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States, 1/7/08.
Ogawa H, Babinsky H. Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets. In 46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. 2008-0599. (46th AIAA Aerospace Sciences Meeting and Exhibit).
Ogawa, Hideaki ; Babinsky, H. / Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets. 46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. (46th AIAA Aerospace Sciences Meeting and Exhibit).
@inproceedings{2a8fb5f0d48f4c8c9c43ac64a4cbd481,
title = "Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets",
abstract = "The effects of three dimensional bump control on separated shock-wave / boundarylayer interactions have been investigated experimentally at M ∞ = 1.5, aiming to reduce total pressure losses incurred by strong normal shock / boundary-layer interactions. Such a situation occurs, for example, inside mixed-compression supersonic engine inlets or on external-compression inlets. Various bump configurations have been tested and their effects have been evaluated in various aspects such as total pressure recovery and boundary-layer thickness. Without control, the normal shock caused a region of relatively two-dimensional separation. Three-dimensional bumps commonly broke up this separation into individual regions of attached and separated flow, giving an overall reduction of the magnitude of separation. Fairly two-dimensional λ-shock structures and streamwise vortex pairs have been observed in all tested configurations. A configuration comprising multiple long, high, narrow rounded bumps has demonstrated the best performance, producing an appreciable total pressure saving as much as 30{\%} owing to a λ-shock benefit with minimum viscous penalty from localised separation.",
author = "Hideaki Ogawa and H. Babinsky",
year = "2008",
month = "12",
day = "1",
language = "English",
isbn = "9781563479373",
series = "46th AIAA Aerospace Sciences Meeting and Exhibit",
booktitle = "46th AIAA Aerospace Sciences Meeting and Exhibit",

}

TY - GEN

T1 - Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets

AU - Ogawa, Hideaki

AU - Babinsky, H.

PY - 2008/12/1

Y1 - 2008/12/1

N2 - The effects of three dimensional bump control on separated shock-wave / boundarylayer interactions have been investigated experimentally at M ∞ = 1.5, aiming to reduce total pressure losses incurred by strong normal shock / boundary-layer interactions. Such a situation occurs, for example, inside mixed-compression supersonic engine inlets or on external-compression inlets. Various bump configurations have been tested and their effects have been evaluated in various aspects such as total pressure recovery and boundary-layer thickness. Without control, the normal shock caused a region of relatively two-dimensional separation. Three-dimensional bumps commonly broke up this separation into individual regions of attached and separated flow, giving an overall reduction of the magnitude of separation. Fairly two-dimensional λ-shock structures and streamwise vortex pairs have been observed in all tested configurations. A configuration comprising multiple long, high, narrow rounded bumps has demonstrated the best performance, producing an appreciable total pressure saving as much as 30% owing to a λ-shock benefit with minimum viscous penalty from localised separation.

AB - The effects of three dimensional bump control on separated shock-wave / boundarylayer interactions have been investigated experimentally at M ∞ = 1.5, aiming to reduce total pressure losses incurred by strong normal shock / boundary-layer interactions. Such a situation occurs, for example, inside mixed-compression supersonic engine inlets or on external-compression inlets. Various bump configurations have been tested and their effects have been evaluated in various aspects such as total pressure recovery and boundary-layer thickness. Without control, the normal shock caused a region of relatively two-dimensional separation. Three-dimensional bumps commonly broke up this separation into individual regions of attached and separated flow, giving an overall reduction of the magnitude of separation. Fairly two-dimensional λ-shock structures and streamwise vortex pairs have been observed in all tested configurations. A configuration comprising multiple long, high, narrow rounded bumps has demonstrated the best performance, producing an appreciable total pressure saving as much as 30% owing to a λ-shock benefit with minimum viscous penalty from localised separation.

UR - http://www.scopus.com/inward/record.url?scp=78149438972&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=78149438972&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:78149438972

SN - 9781563479373

T3 - 46th AIAA Aerospace Sciences Meeting and Exhibit

BT - 46th AIAA Aerospace Sciences Meeting and Exhibit

ER -