NACA-RM-A51H20 REV A

Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:43:52Z
date available	2017-09-04T15:43:52Z
date copyright	01/01/1951
date issued	1951
identifier other	PNMCWDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/46219
description abstract	INTRODUCTION The scoop-type inlet and the NACA submerged inlet are two current inlet designs which supply air to a jet engine and require a relatively short internal ducting. An NACA submerged inlet has been previously tested at transonic speeds (references 1 and 2), but no previous transonic tests of a scoop inlet are known. The purpose of this Investigation was to compare-the transonic characteristics of a scoop-type inlet with those of a submerged inlet. To provide a basis of comparison, the inlets were each mounted in the as me half body, the model being identical from the leading edge of the entrance lip rearward with either inlet mounted in the body. The model was tested on the transonic bump of the Ames 16-foot high-speed wind tunnel. The average Mach number over the bump test section ranged from 0.79 to 1.12.
language	English
title	NACA-RM-A51H20 REV A	num
title	Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds	en
type	standard
page	65
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1951
contenttype	fulltext