Numerical and experimental investigations of a nonslender delta wing with leading-edge vortex flap

Cai, Jinsheng; Pan, Shucheng; Li, Wenfeng; Zhang, Zhengke

doi:10.1016/j.compfluid.2014.03.011

Cited by 10 publications

(4 citation statements)

References 39 publications

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“…Time discretization is done based on the second-order accuracy backward-difference method. The SST turbulence model is applied as the computational model [ 14 , 15 ].…”

Section: The Computation Of Chaff Adiabatic Wall Temperature By Compumentioning

confidence: 99%

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Numerical and experimental study of pyrophoric activated metal Mg surface combustion characteristics

et al. 2018

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The combustion of multi-hole pyrophoric activated metal is solid combustion and the combustion mechanism is quite complex, which is a difficult problem to be solved. Once the pyrophoric activated metal is exposed to air, the oxygen diffuses to the interior of the activated metal within plenty of holes and reacts with it, which enlarges the contact area with oxygen. Consequently, the whole combustion is vigorous and the temperature rises rapidly. To study the combustion mechanism of the chaff, the surface heat balance equation is established in this work by taking Mg as the activated metal. To solve this equation, the chaff adiabatic wall temperature distribution is computed by computational fluid dynamics in the presence of high-speed airflow. Then, the chaff surface temperature distribution is obtained by solving the heat balance equations. Finally, numerical and experimental results obtained via an infrared thermal imager are compared to demonstrate the effectiveness of the established equation.

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“…Time discretization is done based on the second-order accuracy backward-difference method. The SST turbulence model is applied as the computational model [ 14 , 15 ].…”

Section: The Computation Of Chaff Adiabatic Wall Temperature By Compumentioning

confidence: 99%

“…Time discretization is done based on the second-order accuracy backward-difference method. The SST turbulence model is applied as the computational model [14,15]. Setting the diameter of the chaff as 50 mm, the computational zone is a cube with a side length of 5000 mm.…”

Section: The Computation Of Chaff Adiabatic Wall Temperature By Computational Fluid Dynamicsmentioning

confidence: 99%

Numerical and experimental study of pyrophoric activated metal Mg surface combustion characteristics

et al. 2018

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“…Computational modeling of vortex breakdown on a delta wing, with a technique developed based on the use of jet-flaps, is capable of capturing the vortex breakdown location for a variety of jet exit angles (Vlahostergios et al 2013). Numerical and experimental investigations of a non-slender delta wing have examined the leading-edge vortex flap effect (Cai et al 2014). In-depth research about design (Bitencourt et al 2011), control, the interaction between systems, and measuring tools continues to press forward.…”

Section: Introductionmentioning

confidence: 99%

Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Sutrisno

Deendarlianto

Rohmat

et al. 2020

J.Aerosp. Technol. Manag.

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The choice for using a fighter fuselage in a fighter jet design affects a vortex generation advantageous in maneuverability. To study the effect of straight-body-type-fuselage (SBTF) on the vortex dynamic, a computational fluid dynamics (CFD) method is used, in order to simulate a model of SBTF fighter. The simulation uses Q-criterion to probe vortices, and a logarithmic grid to emphasize the micro-gridding effect of the turbulent boundary layer. The results show detailed quantitative velocity, pressure, trajectory of the vortex core, and wing negative surface pressure distribution (SPD), providing clear pictures of opportunity for performance improvement, better lift, agility, and maneuverability of a fighter if a model requires a new design.

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“…Vortex breakdown occurs after the flow separation on the wing by increasing angle of attack [6] has a dominant effect [4][5] on flight conditions and must be examined. Increasing the angle of attack [7] is one of the dominant sources that cause to formation of vortex breakdown and affects [3,8] the whole flow regime around the wing. Vortex breakdown structure includes strong reversed flow [9][10] that occurs on sudden expansion of leading-edge vortices at a critical angle of attack [11][12] in unsteady flows.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Yavuz¹

2020

Journal of Thermal Engineering

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It is well known in literature that further stages of flow separation and vortex breakdown around wings can be able to cause stall of wings. These formations must be investigated carefully for new plane types. However, some limited studies are available, especially on lambda wing for high angles of attack. In this study, effect of angle of attack on flow characteristics and vortex breakdown around a lambda wing is investigated with a constant Reynolds number of 10000. Computational fluid dynamic analysis is used and results of high angles of attack of the wing are given up to 45 0 which are not available in literature. Open water channel simulation is used. Vortex breakdown initially begins at an angle of 17 0 and it almost reaches to tip of wing when angle of attack is equal to 25 0. Vortices get stronger at further increments of angle of attack and they become to nearly equal length of wing at 45 0. Rounding effect of leading edges is investigated for decreasing vortex magnitudes. Streamline, particle injection, iso-value of vortices and location of stagnation points are given, and they are discussed in detail.

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Numerical and experimental investigations of a nonslender delta wing with leading-edge vortex flap

Cited by 10 publications

References 39 publications

Numerical and experimental study of pyrophoric activated metal Mg surface combustion characteristics

Numerical and experimental study of pyrophoric activated metal Mg surface combustion characteristics

Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

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