국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experiments to Ascertain the Bluntness Effect on Attachment Line Transition of a Yawed Cylinder in Hypersonic Flow
저자	FUJII Keisuke, KOYAMA Tadao, TSUDA Syouichi, HIRABAYASHI Noriaki, SEKINE Hideo, NAGAI Shinji, SAKAKIBARA Seizou, HOZUMI Kouichi
Keyword	Compressible flow; boundary layer transition
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltm0000753.pdf?id=NALTM0000753
보고서번호	NAL TM-753
발행년도	2000.10
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Experiments on attachment line transition of two yawed cylinder models with a sharp and a hemisphere nose were conducted in a hypersonic wind tunnel. The tests were conducted at a free-stream Mach number of 7.1, free-stream Reynolds number based on cylinder diameter varying from 0.1×106 to 1.3×106 and angles of attack of 30deg, 40deg and 50deg. Results for the sharp nose model tests matched those of other hypersonic wind tunnel tests. Tests for the hemisphere nose model at α=30deg showed nose bluntness to have a greater effect on transition than expected, based on the entropy layer swallowing effect, while at α=50deg, the effect was close to that expected. The bluntness effect at an angle of attack of 40deg showed the opposite tendency to the other cases.