국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	A Study of Three-Dimensional Interaction Flow Fields between Swept Shock Waves and Turbulent Boundary Layers～Flow Structures and Effects of Bleed～
저자	Masato TAMAYAMA, Kimio SAKATA, Ryoji YANAGI, Shigemi SHINDO, Akira MURAKAMI, Shinji HONAMI
Keyword	Supersonic Flow; Turbulent Boundary Layer; Shock Wave/Boundary Layer Interaction; Air-Bleed Effect
URL	http://send.nal.go.jp/send/jpn/dlfile.php3/naltr01227?doctype=7&filetype=20&path0=naltr01227&path1=pdf&path2=naltr01227.pdf
보고서번호	NAL TR-1227
발행년도	1994.3
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	An experimental investigation of a three-dimensional flow field with a swept shock wave and a turbulent boundary layer interaction was made in NAL’s 1m×1m Mach 4 supersonic wind tunnel.The emphasis of this study is placed on understanding the behaviors of the flow interaction with Mach number variation and the effects of bleed on the surface flow.A shock generator of 15°wedge placed normally on the flat plate was applied to generate an oblique shock wave.The experiments were conducted at Mach numbers of 3.25, 3.11, and 2.63.We adopted the conical coordinate system to analyze the flow.Air-bleed was also tested utilizing rows of bleed holes located at the foot print of the swept shock wave on the flat plate surface.It is generally accepted that the size and the strength of the separation vortex generated along the shock wave on the surface bocome wider and stronger as the Mach number increses.The corner flow around the leading edge of the shock generator was also clarified.As for the air-bleed,the suession effects of the bleed on the separation vortex were also clarified at several bleed locations.The bleed upstream of the shock wave foot print was effectively reduced the size of the vortex,while the downstream bleed suppressed the vortex strength.Therefore,it is concluded that the combination of the upstream and downstream bleed effectively suppresses the interaction between the shock wave and the boundary layer.