NACA-TR-1049

NASA - National Aeronautics and Space Administration (NASA)

Experimental investigation of the effect of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces

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NASA - National Aeronautics and Space Administration (NASA)

Year: 1951

Abstract: An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45º. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory. A reduction in area of vertical tails (geometric aspect ratio kept constant) attached to a given fuselage resulted in an increase in the effective aspect ratio of the vertical tail for the range of tail sizes considered. Simple analytical considerations indicate, however, that for tail sizes below the range investigated the opposite effect would be expected.
For the fuselage-tail combinations investigated, the tail effectiveness usually decreased with increasing angle of attack, with the greatest rate of decrease occurring at angle of attack greater than about 16º.

URI: http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/203275

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	2017-09-04T18:20:49Z
date available	2017-09-04T18:20:49Z
date copyright	01/01/1951
date issued	1951
identifier other	HXDZYDAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/203275
description abstract	An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45º. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory. A reduction in area of vertical tails (geometric aspect ratio kept constant) attached to a given fuselage resulted in an increase in the effective aspect ratio of the vertical tail for the range of tail sizes considered. Simple analytical considerations indicate, however, that for tail sizes below the range investigated the opposite effect would be expected. For the fuselage-tail combinations investigated, the tail effectiveness usually decreased with increasing angle of attack, with the greatest rate of decrease occurring at angle of attack greater than about 16º.
language	English
title	NACA-TR-1049	num
title	Experimental investigation of the effect of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces	en
type	standard
page	29
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1951
contenttype	fulltext
subject keywords	AERODYNAMIC
subject keywords	ASSEMBLIES
subject keywords	COEFFICIENTS
subject keywords	COMPUTATIONAL
subject keywords	CONFIGURATIONS
subject keywords	DYNAMICS
subject keywords	FLUID
subject keywords	FUSELAGES
subject keywords	INTERFERENCE
subject keywords	LATERAL
subject keywords	LENGTH
subject keywords	LIFT
subject keywords	MOMENTS
subject keywords	PITCHING
subject keywords	SHAPES
subject keywords	STABILITY
subject keywords	STABILIZERS
subject keywords	STATIC
subject keywords	SURFACES
subject keywords	SWEPTBACK
subject keywords	TAIL
subject keywords	WINGS