Experimental investigation of 3D shock / boundary layer interaction control in transonic flows

Hideaki Ogawa, H. Babinsky

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

5 Citations (Scopus)

Abstract

A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M = 1.3 and M = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Pages10486-10497
Number of pages12
Publication statusPublished - Dec 1 2006
Externally publishedYes
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
Duration: Jan 9 2006Jan 12 2006

Publication series

NameCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Volume14

Conference

Conference44th AIAA Aerospace Sciences Meeting 2006
CountryUnited States
CityReno, NV
Period1/9/061/12/06

Fingerprint

Transonic flow
transonic flow
shock wave
boundary layers
Boundary layers
boundary layer
shock
Shock waves
wind tunnel
Wind tunnels
shock waves
supersonic wind tunnels
normal shock waves
interactions
Flow interactions
wind tunnel tests
drag reduction
drag
Drag reduction
visualization

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Ogawa, H., & Babinsky, H. (2006). Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting (pp. 10486-10497). (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting; Vol. 14).

Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. / Ogawa, Hideaki; Babinsky, H.

Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. 2006. p. 10486-10497 (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting; Vol. 14).

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

Ogawa, H & Babinsky, H 2006, Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. in Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting, vol. 14, pp. 10486-10497, 44th AIAA Aerospace Sciences Meeting 2006, Reno, NV, United States, 1/9/06.
Ogawa H, Babinsky H. Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. 2006. p. 10486-10497. (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting).
Ogawa, Hideaki ; Babinsky, H. / Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. 2006. pp. 10486-10497 (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting).
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