NACA-WR-L-23

Variation with Mach number of static and total pressures through various screens

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:18:03Z
date available	2017-09-04T18:18:03Z
date copyright	01/01/1946
date issued	1946
identifier other	HQONEEAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/200800
description abstract	Tests were conducted in the Langley 24-inch high-speed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire diameter for an installation so that the choking Mach number is not approached at the maximum operating velocity.
language	English
title	NACA-WR-L-23	num
title	Variation with Mach number of static and total pressures through various screens	en
type	standard
page	28
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1946
contenttype	fulltext