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Characterization and Control of Shock Waves and Compressible Turbulent Boundary Layers through Supersonic Rectangular Ducts

Research Project

Project/Area Number 12650152
Research Category

Grant-in-Aid for Scientific Research (C)

Allocation TypeSingle-year Grants
Section一般
Research Field Fluid engineering
Research InstitutionMURORAN INSTITUTE OF TECHNOLOGY

Principal Investigator

SUGIYAMA Hiromu  Muroran Institute of Technology Dept. of Mechanical Systems Engineering Professor, 工学部, 教授 (70002938)

Co-Investigator(Kenkyū-buntansha) MIZOBATA Kazuhide  Muroran Institute of Technology Dept. of Mechanical Systems Engineering Assistant Professor, 工学部, 講師 (00271875)
ARAI Takakage  Muroran Institute of Technology Dept. of Mechanical Systems Engineering Associate Professor, 工学部, 助教授 (10175945)
Project Period (FY) 2000 – 2001
Project Status Completed (Fiscal Year 2001)
Budget Amount *help
¥3,600,000 (Direct Cost: ¥3,600,000)
Fiscal Year 2001: ¥1,500,000 (Direct Cost: ¥1,500,000)
Fiscal Year 2000: ¥2,100,000 (Direct Cost: ¥2,100,000)
KeywordsPseudo Shock Waves / Shock-Boundary Layer Interaction / Supersonic Flow / Turbulent Flow / Laser Doppler Velocimetry / Particle Imaging Velocimetry / Schlieren Method / SCRAM Jet Engine
Research Abstract

To Investigate the supersonic flow phenomena related to internal and external flows of high pressure gas pipeline systems, air breathing engines and space planes, an experimental study was carried out on shock wave/boundary layer interaction (pseudo shock wave, or PSW) in a rectangular duct, using a supersonic wind tunnel (pressure vacuum type, Mach4.0 and 2.0). A PSW was visualized by schlieren photography. Detailed distribution of velocity in the PSW was measured by particle imaging velocimetry (PIV). Boundary layer separation after the front shock wave occurred more severely on one of the upper and lower walls than on the other, producing an asymmetric flow field. Deceleration of the core flow around the centerline of the duct was small.
Additionally, in order to clarify characteristics of supersonic intakes for ramjet engines, flow structure around and through a small external-compression rectangular intake model with double ramps designed for Mach number 1.9 was investigated experimentally using a vacuum-type wind tunnel and a set of measurement methods composed of colored schlieren photography, laser Doppler velocimetry, and mercury manometry. A critical operation, where shocks induced by ramps attach to the leading edge of the cowl, was attained. A flow plug installed on the downward edge of the intake enabled monotonous compression through a shock train caused by shock-boundary layer interactions.

Report

(3 results)
  • 2001 Annual Research Report   Final Research Report Summary
  • 2000 Annual Research Report
  • Research Products

    (5 results)

All Other

All Publications (5 results)

  • [Publications] 杉山弘, 溝端一秀, 新井隆景, 福田浩一, 孫立群, 遠藤清和, 広島敬之: "室蘭工業大学新設マッハ4超音速風洞の気流特性および衝撃波と乱流境界層の干渉現象に関する研究"室蘭工業大学紀要. 第51号. 57-62 (2001)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] 溝端一秀, 杉山弘, 荒川岳史, 辰己薫, 小倉栄二, 倉田良治: "ラムジェットエンジン用超音速空気取り入れ口における流れ構造と空力特性"室蘭工業大学紀要. 第51号. 69-75 (2001)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Hiromu SUGIYAMA, Kazuhide MIZOBATA, Takakage ARAI, Koukhi FUKUD, SUN Li Qun, Kiyokazu ENDO, Takayuki HIROSHIMA: "Flow Characteristics of the New Mach 4 Supersonic Wind Tunnel of Muroran Institute of Technology and Study on Shock Wave and Turbulent Boundary Layer Interactions"Memories of the Muroran Institute of Technology. Vol. 51. 57-62 (2001)

    • Description
      「研究成果報告書概要(欧文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Kazuhide MIZOBATA, Hiromu SUGIYAMA, Takeshi ARAKAWA, Kaoru TATSUMI, Eiji OGURA, Ryoji KURATA: "Flow Structure and Aerodynamic Characteristics in a Supersonic Intake for Ramjet Propulsion"Memories of the Muroran Institute of Technology. Vol. 51. 69-75 (2001)

    • Description
      「研究成果報告書概要(欧文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] 杉山弘, 溝端一秀, 新井隆景, 福田浩一, 孫立群, 遠藤清和, 広島敬之: "室蘭工業大学新設マッハ4超音速風洞の気流特性および衝撃波と乱流境界層の干渉現象に関する研究"室蘭工業大学紀要. 第51号. 57-62 (2001)

    • Related Report
      2001 Annual Research Report

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Published: 2000-04-01   Modified: 2016-04-21  

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