NASA-TN-D-209

NASA - National Aeronautics and Space Administration (NASA)

The rolling moment due to sideslip of swept wings at subsonic and transonic speeds

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NASA - National Aeronautics and Space Administration (NASA)

Year: 1960

Abstract: An analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.
In view of the need for reliable procedures for estimating rolling moment due to sideslip at high subsonic speeds, new methods have been derived and design charts are presented for estimating the effects of compressibility and wing geometry. The overall agreement between estimated and experimental results indicated that the effects of win g aspect ratio, taper ratio, sweep, and dihedral on the rolling moment due to side-slip of wing-fuselage configurations for sideslip angles up to ±5° could be estimated with reasonable accuracy up to the force-break Mach number at low lift coefficients.

URI: https://yse.yabesh.ir/std/handle/yse/105374

Subject: ASPECT

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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	2017-09-04T16:42:04Z
date available	2017-09-04T16:42:04Z
date copyright	01/01/1960
date issued	1960
identifier other	VQTKAEAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/105374
description abstract	An analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range. In view of the need for reliable procedures for estimating rolling moment due to sideslip at high subsonic speeds, new methods have been derived and design charts are presented for estimating the effects of compressibility and wing geometry. The overall agreement between estimated and experimental results indicated that the effects of win g aspect ratio, taper ratio, sweep, and dihedral on the rolling moment due to side-slip of wing-fuselage configurations for sideslip angles up to ±5° could be estimated with reasonable accuracy up to the force-break Mach number at low lift coefficients.
language	English
title	NASA-TN-D-209	num
title	The rolling moment due to sideslip of swept wings at subsonic and transonic speeds	en
type	standard
page	82
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1960
contenttype	fulltext
subject keywords	ASPECT
subject keywords	BODY
subject keywords	COMPRESSIBILITY
subject keywords	CONFIGURATIONS
subject keywords	GEOMETRY
subject keywords	MACH
subject keywords	MOMENTS
subject keywords	NUMBER
subject keywords	RATIO
subject keywords	ROLLING
subject keywords	SIDESLIP
subject keywords	SPEED
subject keywords	SUBSONIC
subject keywords	SWEPT
subject keywords	TESTS
subject keywords	TRANSONIC
subject keywords	TUNNEL
subject keywords	WIND
subject keywords	WING
subject keywords	WINGS