국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experimental Studies of Supersonic Film Cooling with Shock Wave
저자	Fumiei ONO, Takeshi KANDA, Masahiro TAKAHASHI, Toshihito SAITO, Yoshio WAKAMATSU
Keyword	Film Cooling; Mixing; Slot Injection; Supersonic FLow; Shock Wave; Turbulent Boudary Layer
URL	http://send.nal.go.jp/send/jpn/dlfile.php3/naltr01276?doctype=7&filetype=20&path0=naltr01276&path1=pdf&path2=naltr01276.pdf
보고서번호	NAL TR-1276
발행년도	1995.9
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Supersonic film cooling was tested in the Mach 2.35 wind tunnel to investigate the effect of the external shock wave on film cooling.The coolant was injected at sonic speed.The weak shock wave,whose pressure ratio was 1.21,did not reduce the film cooling effectiveness.The stronmeprature in the interacting region.In the region of the interation,energy and mass were not transferred,but the momentum was transferred from the primary flow to the coolant.