NACA-TN-3394

Low-speed investigation of the effects of angle of attack on the pressure recovery of a circular nose inlet with several lip shapes

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:53:04Z
date available	2017-09-04T16:53:04Z
date copyright	01/01/1955
date issued	1955
identifier other	WUNUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/116465
description abstract	Wind-tunnel tests wee conducted to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0° to 25°. A sharp inlet lip having a wedge angle of 7-½° was tested in addition to two circular-arc profiles and two elliptical profiles formed within the wedge of the sharp lip by cutting back the leading edge various amounts. It was found that for a given amount of cutback, the circumferential variation of total pressure at the measuring station (the simulated entrance to a turbojet-engine compressor) was about the same with either an elliptical- or circular-arc-profile lip; however, the average total-pressure recovery characteristics were better with the elliptical-profile lip.
language	English
title	NACA-TN-3394	num
title	Low-speed investigation of the effects of angle of attack on the pressure recovery of a circular nose inlet with several lip shapes	en
type	standard
page	31
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1955
contenttype	fulltext