국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Numerical Calculation of Scramjet Inlet Flow
저자	Tomiko ISHIGURO, Satoru OGAWA, Yasuhiro WADA
Keyword	hypersonic flow; supersonic flow; scramjet inlet
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr1174t.pdf?id=NALTR0001174T
보고서번호	NAL TR-1174T
발행년도	1992.7
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	braic turbulent model are solved by applying the TVD scheme to the uniform mesh points of the space.To exhibit capability of the numerical procedure,parametric studies on flow simulations were carried out by fixing freestream Reynolds number Re=Re=ρ∞c∞L/μ∞=5.3×105 under various trios of a freestream Mach number M∞,a sweep angle of leading edge of side plate β,and an entrance/throat contaction ratio R(M∞=2～10,β=0 ～60 ,R=3～10).The influence of the parameters on inlet performances(a mass capture ratio,a total pressure recovery ratio,and possibility of starting)is discussed.The results are in good agreements with the experiments under M∞=4 in starting cases,where iterated reflective oblique shock waves made by wedges of side panels decelerate and compress air.Unstarting phenomenon was analyzed in cases either of low M∞ or high R.To addition,an unstarting flowfield was obtained in the computation of incoming flow condition with a thich boundary layer attached to the upper wall or with a small freeumber.If the unstarting was caused by viscosity,a large subsonic recirculation region grows just under the upper wall in upstream region of the throat.A separation shock wave which emanates from the upstream end of region prevents the formation of a interative weak shock wave system.