NACA-TR-1193

NASA - National Aeronautics and Space Administration (NASA)

Theoretical performance characteristics of sharp-lip inlets at subsonic speeds

Organization:

NASA - National Aeronautics and Space Administration (NASA)

Year: 1954

Abstract: SUMMARY
A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, base on a simple momentum balance consideration, permits the computation of inlet-pressure-recovery–mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound.
The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at he take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. Experimental data obtained at zero speed with a sharp-lip super-sonic inlet model were in substantial agreement with the theoretical results.

URI: https://yse.yabesh.ir/std/handle/yse/3921

Subject: AERODYNAMIC

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NASA - National Aeronautics and Space Administration (NASA)

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contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:06:21Z
date available	2017-09-04T15:06:21Z
date copyright	01/01/1954
date issued	1954
identifier other	LERXYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/3921
description abstract	SUMMARY A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, base on a simple momentum balance consideration, permits the computation of inlet-pressure-recovery–mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at he take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. Experimental data obtained at zero speed with a sharp-lip super-sonic inlet model were in substantial agreement with the theoretical results.
language	English
title	NACA-TR-1193	num
title	Theoretical performance characteristics of sharp-lip inlets at subsonic speeds	en
type	standard
page	12
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1954
contenttype	fulltext
subject keywords	AERODYNAMIC
subject keywords	AIR
subject keywords	AIRCRAFT
subject keywords	ANALYSIS
subject keywords	ANGLE
subject keywords	ATTACK
subject keywords	COEFFICIENTS
subject keywords	CORRELATION
subject keywords	DESIGN
subject keywords	DRAG
subject keywords	EXPERIMENTATION
subject keywords	FLOW
subject keywords	INTAKES
subject keywords	MASS
subject keywords	PERFORMANCE
subject keywords	PREDICTION
subject keywords	PRESSURE
subject keywords	RECOVERY
subject keywords	SHARPNESS
subject keywords	SPEED
subject keywords	SUBSONIC
subject keywords	SUPERSONIC
subject keywords	TECHNIQUES
subject keywords	THEORIES
subject keywords	ZERO