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

通过超音速矩形管道的冲击波和可压缩湍流边界层的表征和控制

• 批准号: 12650152
• 负责人: SUGIYAMA Hiromu
• 金额: $ 2.3万
• 依托单位: MURORAN INSTITUTE OF TECHNOLOGY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2000
• 资助国家: 日本
• 起止时间: 2000 至 2001
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-12650152/
• 关键词: Pseudo Shock Waves; Shock-Boundary Layer Interaction; Supersonic Flow; Turbulent Flow; Laser Doppler Velocimetry; Particle Imaging Velocimetry; Schlieren Method; SCRAM Jet Engine

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.

为了研究高压燃气管道系统、吸气式发动机和航天飞机内外流的超声速流动现象，利用压力真空型马赫数为4.0和2.0的超声速风洞，对矩形管道内激波/边界层干扰（伪激波，PSW）进行了实验研究。一个PSW可视化纹影摄影。利用粒子成像测速仪（PIV）测量了PSW内的速度分布。前激波后的边界层分离在上壁和下壁中的一个上比另一个上更严重，从而产生不对称流场。另外，为了研究冲压发动机进气道的特性，采用彩色纹影摄影技术和真空式风洞，对马赫数为1.9的双斜面外压式矩形进气道模型进行了实验研究，激光多普勒测速仪和水银测压仪。一个关键的操作，其中诱导的冲击附加到前缘的斜坡，获得。安装在进气道下沿的流动塞通过激波-边界层相互作用引起的激波串实现单调压缩。

项目成果

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)

Hiroshi Sugiyama、Kazuhide Mizobata、Takakage Arai、Koichi Fukuda、Tategun Son、Kiyokazu Endo、Noriyuki Hiroshima：“室兰工业大学新建的4马赫超音速风洞中的气流特性及激波与湍流边界层的干涉现象研究室兰工业大学公报第 51. 57-62 号 (2001)

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 (200

Kazuhide MIZOBATA、Hiromu SUGIYAMA、Takeshi ARAKAWA、Kaoru TATSUMI、Eiji OGURA、Ryoji KURATA：“冲压喷气发动机推进超音速进气的流动结构和空气动力特性”室兰工业大学的回忆。

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)

Kazuhide Mizobata、Hiroshi Sugiyama、Takeshi Arakawa、Kaoru Tatsumi、Eiji Ogura、Ryoji Kurata：“冲压喷气发动机超音速进气口的流动结构和空气动力特性”室兰工业大学通报第 51. 69-75 号。 ) )

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 Boundar

Hiromu SUGIYAMA、Kazuhide MIZOBATA、Takakage ARAI、Koukhi FUKUD、孙立群、Kiyokazu ENDO、Takayuki HIROSHIMA：《室兰工业大学新型马赫 4 超音速风洞的流动特性及冲击波和湍流边界研究》