NACA-TN-3663

Discharge coefficients for combustor-liner air-entry holes

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:00:50Z
date available	2017-09-04T18:00:50Z
date copyright	01/01/1956
date issued	1956
identifier other	FXONEEAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/183810
description abstract	An experimental investigation was conducted t o determine the effects of various geometric and flow factors on the discharge coefficients for circular holes having flow parallel to the plane of the hole. The geometric and flow factors considered were hole diameter, wall thickness at the at the hole, parallel-flow duct height, boundary-layer thickness, parallel-flow velocity, static-pressure level, and pressure ratio across the test hole. Discharge coefficients, corrected for pressure-ratio effects, were correlated with a flow parameter incorporating the total and static pressures of the discharge jet and of the parallel-flow stream. Within the range investigated, the effects of hole diameter and wall thickness at the hole on discharge coefficients were small compared with the effects of parallel-flow velocity and static-pressure ratio across the hole. The effects of duct height, boundary-layer thickness, and static-pressure level were negligible.
language	English
title	NACA-TN-3663	num
title	Discharge coefficients for combustor-liner air-entry holes	en
type	standard
page	40
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1956
contenttype	fulltext