The impact of the pitching motion on the structure of the vortical flow over a slender delta wing under sideslip angle

Tasci, Mehmet Oguz; Pektas, Mehmet Can; Tümse, Sergen; Karasu, İlyas; Şahi̇n, Beşi̇r; Akıllı, Hüseyin

doi:10.1007/s12650-020-00720-4

Cited by 6 publications

(3 citation statements)

References 13 publications

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“…In order to simplify the problem, only the internal flow characteristics of the inlet during pitch maneuver and yaw maneuver are investigated [41][42][43]. In the course of pure pitch maneuver with constant incoming flow conditions, the angle of attack of the aircraft is equal to the angle of pitch; The angle of attack of the aircraft is equal to the sideslip angle during the simple yaw maneuver with the inflow conditions unchanged.…”

Section: Analysis Of Transient Flow Characteristicsmentioning

confidence: 99%

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Zhang

2023

Applied Sciences

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Submerged inlet has been widely used in UAVs and cruise missiles due to its good stealth characteristics, but it also brings the disadvantage of poor aerodynamic characteristics. Especially in large maneuvering flight, the flow field near the fuselage has a strong unsteady effect, and the total pressure recovery coefficient and distortion characteristics have deteriorated sharply. In order to investigate the steady and transient aerodynamic characteristics of the submerged inlet in large maneuver flight and improve its maneuver envelope, a design scheme of a distributed submerged inlet for large maneuver flight is proposed in this paper. Taking a cruise missile as the research object, the steady and transient analysis of the conventional submerged inlet and the distributed submerged inlet is carried out using CFD numerical method. The results show that the distributed submerged inlet can significantly improve the inlet performance and enhance the sideslip limit of the submerged inlet during large sideslip maneuver flight. When the sideslip angle is 30°, compared with the conventional submerged inlet configuration, the outlet total pressure recovery coefficient of the distributed submerged inlet configuration is increased by 44.2%, and the total pressure distortion index is reduced by 66.3%.

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Section: Analysis Of Transient Flow Characteristicsmentioning

confidence: 99%

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Zhang

2023

Applied Sciences

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“…Additionally, as previously discussed, during landing and takeoff, the aircraft is in close proximity to the ground; this further influences the aircraft's aerodynamics and stability behavior. Several studies [39][40][41][42][43][44] have discussed the flow physics associated with various types of ground effects; they predicted the effects of various ground effects on the aerodynamics and stability parameters.…”

Section: Flight Dynamic Modelsmentioning

confidence: 99%

Flight Dynamic Characteristics of Wide-Body Aircraft with Wind Gust and Turbulence

Mehmood,

Ali Shah,

Ali Shams

et al. 2023

Fluids

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In this research, a wide-body aircraft was analyzed with critical monitoring of its states, a function of several control inputs (wind gust, turbulence, and microburst). The aerodynamic and stability coefficients of a Boeing 747-200 were obtained from previously published works and 6- DOF equations were formulated. Simulations were conducted for various control inputs to determine the aircraft’s free response, as well as the forced response. In order to understand the nature of the atmosphere, three different models were incorporated, including (i) the Dryden Model, (ii) wind gust, and (iii) microburst. The aircraft was found to be stable in the longitudinal and lateral flight modes, with trim conditions agreeing with published data. For a vertical wind gust of −10 ft/s, the AoA and pitch rate were observed to oscillate sinusoidally and became stable with new trim conditions. These states were found to regain trim conditions once the gust was removed. In the case of 3D gust, it was found that the longitudinal modes achieved a new trim condition through Phugoid oscillations, whereas the lateral modes underwent short-period oscillations. For the case of turbulence, random fluctuations were observed for trim conditions with no unstable behavior. When considering the microburst case, it was found that the aircraft initially gained altitude in the region of the headwind; this was followed by a sharp descent under the influence of a vertical velocity component.

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“…In addition, the slender body was the basic geometry of fighter aircraft and missiles, hence, the highly random asymmetric flow was coupled with wings and induces a yawing moment [ 3 ], which was even largely great beyond the control by the rudder of a missile [ 2 , 4 , 5 ]. In addition, the development and bursting of asymmetric vortices were sensitive to the structure of the wings and the coupling position at high AoA [ 6 , [7] , [8] ]. During side-force and yawing, the controllability of the aircraft and missile was reduced, thereby resulting in a failed mission because the desired tracks of the fighter aircraft and missiles were changed.…”

Section: Introductionmentioning

confidence: 99%

Investigation of periodic characteristics of perturbed flow over a slender body

Zhao

Wang

2023

Heliyon

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The impact of the pitching motion on the structure of the vortical flow over a slender delta wing under sideslip angle

Cited by 6 publications

References 13 publications

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Flight Dynamic Characteristics of Wide-Body Aircraft with Wind Gust and Turbulence

Investigation of periodic characteristics of perturbed flow over a slender body

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