NACA-RM-L51K09

The effect of surface roughness on the performance of a 23 degree conical diffuser at subsonic Mach numbers

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:39:38Z
date available	2017-09-04T18:39:38Z
date copyright	01/01/1952
date issued	1952
identifier other	JSONEEAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;query=autho162sAF679D40AC421854DD6EFDEC9FCD/handle/yse/221269
description abstract	An investigation was conducted to determine the effect of surface roughness on the performance of a 23º conical diffuser with a 2:1 ratio of edit to inlet area and with a constant-area tail pipe about 3½ inlet diameters in length. The inlet-boundary-layer thickness was of the order of 5 percent of the inlet diameter. The air flows use in this investigation cover an inlet Mach number range from 0.10 to 0.64, corresponding to Reynolds numbers of 10⁶ to 6 X 10⁶ based on inlet diameter. The surface of the diffuser was coated with cork particles of a controlled size. Incremental bands of roughness were removed from the downstream edge after each series of pressure measurements were made and the variation of diffuser performance with percent of diffuser length roughened thereby determined.
language	English
title	NACA-RM-L51K09	num
title	The effect of surface roughness on the performance of a 23 degree conical diffuser at subsonic Mach numbers	en
type	standard
page	44
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1952
contenttype	fulltext