MEASUREMENTS OF HEAT-TRANSFER COEFFICIENTS IN THE INTERACTION REGIONS BETWEEN OBLIQUE SHOCK WAVES AND TURBULENT BOUNDARY LAYERS WITH A MULTI-LAYERED THIN FILM HEAT TRANSFER GAUGE.

Masanori Hayashi, Akira Sakurai, Shigeru Aso

研究成果: ジャーナルへの寄稿記事

4 引用 (Scopus)

抄録

A new type of thin-film heat transfer gauge is applied to the measurements of heat-transfer coefficients in the interaction regions of oblique shock waves and fully developed turbulent boundary layers. It has been developed for the measurement of heat flux with high spatial resolution and fast response for wind tunnels with a long flow duration. Experiments have been performed for a Mach number of 4, a total pressure of 1. 2 MPa, a wall pressure ratio of 0. 59-0. 65, a Reynolds number of (1. 3-1. 5). 10**7, and incident shock angles from 17. 8 to 22. 8 degrees. The flow fields are visualized by the Schlieren technique. Both the surface pressure distributions and the heat transfers are measured throughout theinteraction regions by scanning the shock generator parallel to the freestream. Owing to the high spatial resolution of the new sensor, complicated features of the aerodynamic heating in the interaction region are revealed.

元の言語英語
ページ(範囲)102-110
ページ数9
ジャーナルTransactions of the Japan Society for Aeronautical and Space Sciences
30
発行部数88
出版物ステータス出版済み - 8 1987

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oblique shock waves
turbulent boundary layer
heat transfer coefficients
shock wave
Shock waves
Heat transfer coefficients
Gages
heat transfer
gauge
Boundary layers
spatial resolution
shock
aerodynamic heating
Aerodynamic heating
Heat transfer
Thin films
wall pressure
pressure ratio
high resolution
wind tunnels

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

これを引用

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title = "MEASUREMENTS OF HEAT-TRANSFER COEFFICIENTS IN THE INTERACTION REGIONS BETWEEN OBLIQUE SHOCK WAVES AND TURBULENT BOUNDARY LAYERS WITH A MULTI-LAYERED THIN FILM HEAT TRANSFER GAUGE.",
abstract = "A new type of thin-film heat transfer gauge is applied to the measurements of heat-transfer coefficients in the interaction regions of oblique shock waves and fully developed turbulent boundary layers. It has been developed for the measurement of heat flux with high spatial resolution and fast response for wind tunnels with a long flow duration. Experiments have been performed for a Mach number of 4, a total pressure of 1. 2 MPa, a wall pressure ratio of 0. 59-0. 65, a Reynolds number of (1. 3-1. 5). 10**7, and incident shock angles from 17. 8 to 22. 8 degrees. The flow fields are visualized by the Schlieren technique. Both the surface pressure distributions and the heat transfers are measured throughout theinteraction regions by scanning the shock generator parallel to the freestream. Owing to the high spatial resolution of the new sensor, complicated features of the aerodynamic heating in the interaction region are revealed.",
author = "Masanori Hayashi and Akira Sakurai and Shigeru Aso",
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