Flow Investigation on the Directional Instability of Aircraft with the Single Vertical Tail

Wen, Jia; Xueying, Deng; Wang, Y.K.; Ou, S.

doi:10.1016/j.proeng.2013.12.032

Cited by 2 publications

(2 citation statements)

References 7 publications

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“…Most run of the mill commercial aircrafts with a vertical tail displayed high levels of instability at medium to high angles of attack. J. Wen et al [16] construct and put an aircraft to the test to encapsulate the specific structures of the aircraft contributing to the yawing moment. In order to individually test parts and check its effect on the whole aircraft, they decide to have all the parts be detachable.…”

Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Potty¹,

Angelo²,

Rao

et al. 2019

ujme

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Expressed in nature's infinite subtleties, the Fuselage draws its inspiration from the streamlined body of a bird or a fish, channelizing the flow of air around, enabling its ease in flight. Spanning most of the aircrafts structure, it plays a crucial role in the ferrying of people and cargo, simultaneously balancing the shears due to the empennage and wing structures all in mid-air. Its structural integrity is often questioned by failures due to load or bad air during maneuvers, causing instability which has led many to intensively explore and develop an ideal fuselage. The behaviour of the fuselage is crucially determined by the structural integrity and aerodynamic performance. This paper is an attempt at collating the recent technological advances pertaining to the fuselage. We've streamlined and categorised the wide-ranging scholarly articles by three fundamentally varying approaches-Theoretical, Experimental and Numerical. The theoretical approach saw the authors test out their hypothesis by utilizing and constructing various mathematical models using scientific principles with no verification by actual experimentation or simulation work. The experimental approach pertains to those papers whose authors devised experiments, whose data was used to draw distinct conclusions. The numerical approach mainly dealt with heavy computational analysis using FEM and CFD analysis. Therefore, this paper serves as a compendium for researchers and developers attempting to familiarise themselves with the current advancements and developments in domain of fuselage technology.

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Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Potty¹,

Angelo²,

Rao

et al. 2019

ujme

View full text Add to dashboard Cite

show abstract

“…This paper discusses the details related to aerodynamics forces due to the effects of tail dihedral angle, particularly the effects on the side force coefficient that in turn affect the directional stability and control of the aircraft. The vertical plane design depends on the type of aircraft and the flow regime around it [1,2]. A lot of results on directional stability on isolated vertical tailplanes, even combined to horizontal tails with and without dihedral angles, were obtained through wind tunnel tests by National Advisory Committee for Aeronautics (NACA).…”

Section: Introductionmentioning

confidence: 99%

Effects of Aircraft Tail Configurations on Sensitivity to Yaw Disturbances

Musa

Mansor

Ali

et al. 2014

AMM

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A wind tunnel test was conducted to compare the characteristics of low speed stability and control for aircraft with conventional tail and V-tail configurations. Comparison was made in terms of static directional stability at selected test speed of 40 m/s, which corresponds to Reynolds number of 0.1622 x 106 based on the chord. Three types of simplified tail-only model were tested in Universiti Teknologi Malaysia's Low Speed Wind Tunnel (UTM-LST). Results show that the V-tail configuration greatly affects the aerodynamic characteristics in directional stability as the side force and yaw moment tends to vary linearly with yaw angles up to 25 degrees, compared to conventional tail that has linear characteristics up to only 10 degrees yaw

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Flow Investigation on the Directional Instability of Aircraft with the Single Vertical Tail

Cited by 2 publications

References 7 publications

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Effects of Aircraft Tail Configurations on Sensitivity to Yaw Disturbances

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