국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experimental Studies of Supersonic Film Cooling with Shock Wave Interaction (II)
저자	Fumiei ONO, Takeshi KANDA, Toshihito SAITO, Yoshio WAKAMATSU
Keyword	film cooling; mixing; slot injection; supersonic flow; shock wave; turbulent boundary layer
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr0001340.pdf?id=NALTR0001340
보고서번호	NAL TR-1340
발행년도	1997.12
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Supersonic film cooling was tested in a Mach 2.35 wind tunnel to investigate the effect of external shock waves. The coola maximum wall pressure was lower than the pressure calculated with the oblique shock wave equation. It was confirmed that momentum was transported from the primary flow to the core part of the coolant layer with mass transportation. Based on this result, the interaction between the subsonic film coolant and the supersonic primary flow caused by the shock wave impingement was simulated. With the simulated results, separation of the film coolant was investigated.