Effects of Synthetic Jet Actuator (SJA) on Flow Topology of Blunt-Edged UTM VFE2 Wing Model

Mat, Shabudin; Abdullah, Mohd Azman; Dahalan, Md. Nizam; Said, Mohd Farid Muhamad; Mansor, Shuhaimi; Abdul-Latif, Ainullotfi; Lazim, Tholudin Mat

doi:10.2514/6.2017-0326

Cited by 1 publication

(3 citation statements)

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“…Active and passive flow control techniques are used to modify vortex strength, location and structure [17,18,19,20]. Current research carried out by Fahmi [21] has shown that the flow characteristics above the VFE-2 model can be controlled by a technique called 'blower'. During the experiment, Fahmi [21] has placed the blower at positions of 25% and 65% from the wing apex.…”

Section: Literature Reviewmentioning

confidence: 99%

“…Current research carried out by Fahmi [21] has shown that the flow characteristics above the VFE-2 model can be controlled by a technique called 'blower'. During the experiment, Fahmi [21] has placed the blower at positions of 25% and 65% from the wing apex. However, this study could not confirm that this configuration has successfully brought the primary vortex to the apex of the wing.…”

Section: Literature Reviewmentioning

confidence: 99%

“…1] [8], Luckring [2] [4] and Mat et al[21]. Effect of angle of attack on the onset of the primary vortex at (a) 0.5×10 6 , α= 13.3º, (b) 0.5×106 , α= 18º and (c) 0.5×10 6 , α= 23º.…”

mentioning

confidence: 99%

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Influence of Active Flow Control on Blunt-Edged VFE-2 Delta Wing model

Madan

Tajudin

Said

et al. 2021

IJAME

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This paper highlights the flow topology above blunt-edged delta wing of VFE-2 configuration when an active flow control technique called ‘blower’ is applied in the leading edge of the wing. The flow topology above blunt-edged delta wing is very complex, disorganised and unresolved compared to sharp-edged wing. For the sharp leading-edged wing, the onset of the primary vortex is fixed at the apex of the wing and develops along the entire wing towards the trailing edge. However, the onset of the primary vortex is no longer fixed at the apex of the wing for the blunt-edged case. The onset of the primary vortex develops at a certain chord-wise position and it moved upstream or downstream depending on Reynolds number, angle of attack, Mach number and the leading-edge bluntness. An active flow control namely ‘blower’ technique has been applied in the leading edge of the wing in order to investigate the upstream/downstream progression of the primary vortex. This research has been carried out in order to determine either the flow on blunt-edged delta wing would behave as the flow above sharp-edged delta wing if any active flow control is applied. The experiments were performed at Reynolds number of 0.5×106, 1.0×106 and 2.0×106 corresponding to 9 m/s, 18 m/s and 36 m/s in UTM Low Speed wind Tunnel based on the mean aerodynamic chord of the wing. The results obtained from this research have shown that the blower technique has significant effects on the flow topology above blunt-edged delta wing. The main observation from this study was that the primary vortex has been shifted 20% upstream when the blower technique is applied. Another main observation was the ability of this flow control to delay the formation of the vortex breakdown.

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