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A preliminary investigation of the effects of frequency and amplitude on the rolling derivatives of an unswept-wing model oscillating in roll

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:41:00Z
date available2017-09-04T17:41:00Z
date copyright01/01/1956
date issued1956
identifier otherDWNUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std/handle/yse/163905
description abstractA model with separable wing and tail assembly was oscillated in roll through a range of frequencies and amplitudes of oscillation for an angle of attack of 0° and at one frequency and amplitude for two higher angles of attack in order to determine the effects of the unsteady motion on the rolling stability derivatives of the model and its components.
A variation of frequency or amplitude of oscillation in the range covered at an angle of attack of 0° had no important effect on either the yawing moment due to rolling or the damping in roll for this unsweptwing airplane configuration". The only appreciable value of yawing moment due to rolling was shown by the fuselage-tail combination. This configuration experienced a reduction in magnitude of the derivative as either the frequency or the amplitude of the oscillation increased.
The values of the rolling derivatives obtained by oscillation were consistent with the values measured by means of conventional rolling flow tests at an single of attack of 0°. For the model with the wing at a high angle of attack, the oscillatory yawing moment due to rolling was different from that obtained under steady-state conditions.
languageEnglish
titleNACA-TN-3554num
titleA preliminary investigation of the effects of frequency and amplitude on the rolling derivatives of an unswept-wing model oscillating in rollen
typestandard
page28
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1956
contenttypefulltext


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