Computational modeling of vortex breakdown control on a delta wing

Vlahostergios, Zinon; Missirlis, Dimitris; Yakinthos, K.; Goulas, A.

doi:10.1016/j.ijheatfluidflow.2012.12.002

Cited by 10 publications

(5 citation statements)

References 25 publications

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“…Both vortex structures interact with each other (Abderrahmane 2013). 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).…”

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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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 location of vortex breakdown moves [16] towards the tip of wing by increasing angle of attack and causes to stall, if vortex breakdown reaches to tip of the wing [6,17]. When angle of attack reaches critical values, moment effect [18] on lifting gets vanished from wing surfaces at the separation location of vortices.…”

Section: Introductionmentioning

confidence: 99%

“…But the breakdown is not fully prevented, and high angle of attack causes to flow separations [47] in that application. Jet flaps are [48] investigated by using CFD analysis for prevention of the moment effect in another delaying applications.…”

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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“…Mitchel has learned vortical stream regulation and burst over slender DW. Vlahostergios (Vlahostergios, Missirlis, Yakinthos, & Goulas, 2013) has investigated vortex breakdown control using jet flap.…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis and Visualization of Canard and Fuselage Effects on Flow Patterns around a Straight-Body-Type-Fuselage (SBTF) Fighter Models with Experimental Method in Water Tunnel

Sutrisno¹,

Rs²,

Zainuri³

et al. 2018

MAS

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Performance analysis and visualization of canard and fuselage effects on flow patterns around an SBTF fighter model have been conducted. An SBTF fighter model with an experimental method in a water tunnel would easily reveal visually the vortex dynamics phenomenon that occurred. Testing has been done, with some form of non-canard and canard aircraft in a water tunnel, on vortex dynamics and aerodynamic power on the aircraft model. The stream demonstration used a fluid speed of 0.1 m/s and Reynolds number 6.577x103 on a 1:110 scale model and measured using dye injection method with a print ink type with a mixture ratio of 1:8. The result of the research using GAMA water tunnel showed the aerodynamic force and vortex dynamics phenomenon that happened on the model aircraft. The research on the benefits of the canard is also done by examining the performance and the flow visualization of an SBTF fighter without fuselage, with the symmetrical plane and with the regular fuselage in a water tunnel. The results showed that the use of canard affected the lift, drag, and flow pattern around the wings. The use of canard can enhance the lift of the plane and function to delay the stall by restoring the flow above the wing which should have experienced turbulence back into laminar so that the fighter can maneuver to a higher angle of attack (AoA) without stalling. It is identified that canard and fuselage play significant roles on the design of a fighter. The design choice of the fuselage and the employment of canard are fundamental to support the ability of maneuver and agility of the fighter.

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Computational modeling of vortex breakdown control on a delta wing

Cited by 10 publications

References 25 publications

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

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

Performance Analysis and Visualization of Canard and Fuselage Effects on Flow Patterns around a Straight-Body-Type-Fuselage (SBTF) Fighter Models with Experimental Method in Water Tunnel

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