NACA-RM-L54K18

Investigation of two short annular diffuser configurations utilizing section and injection as a means of boundary-layer control

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:22:14Z
date available	2017-09-04T18:22:14Z
date copyright	01/01/1955
date issued	1955
identifier other	IAPNEEAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;query=autho162s6596FCDCAC4261590-%20Naval%20Facilities%20E/handle/yse/204603
description abstract	The performances of two annular diffuser designs applicable to turbojet afterburner installations were investigated to determine the effectiveness of injection and suction boundary-layer controls. The outer shell was cylindrical in each case. The basic center-body design was an abrupt dump type which produced an equivalent conical diffuser angle of approximately 100⁰. The addition of a conical center-body fairing to the basic design produced a second configuration corresponding to an equivalent conical diffuser angle of 32⁰. Both designs had an area ratio of 1.9:1 and were tested with fully developed pipe flow at the inlet up to a Mach number of 0.45.
language	English
title	NACA-RM-L54K18	num
title	Investigation of two short annular diffuser configurations utilizing section and injection as a means of boundary-layer control	en
type	standard
page	45
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1955
contenttype	fulltext