Parametric investigation of the effects of active flow control on the normal force of a delta wing

2000 ◽  
Author(s):  
Yair Guy ◽  
Julie Morrow ◽  
Thomas McLaughlin ◽  
Israel Wygnanski
Keyword(s):  
Flow Control ◽  
Normal Force ◽  
Delta Wing ◽  
Active Flow Control ◽  
Parametric Investigation ◽  
Active Flow

Active Flow Control on a Nonslender Delta Wing

2008 ◽  
Vol 45 (6) ◽  
pp. 2100-2110 ◽  
Author(s):  
N. M. Williams ◽  
Z. Wang ◽  
I. Gursul
Keyword(s):  
Flow Control ◽  
Delta Wing ◽  
Active Flow Control ◽  
Active Flow

Control of Centrifugal Instability in Vortex-Surface Interaction

2015 ◽  
Author(s):  
Vaibhav Kumar ◽  
Nandeesh Hiremath ◽  
Dhwanil Shukla ◽  
Nikolaus Thorrell ◽  
Narayanan Komerath
Keyword(s):  
Flow Control ◽  
Delta Wing ◽  
Active Flow Control ◽  
Angle Of Attack ◽  
Surface Flow ◽  
Near Surface ◽  
Passive Flow Control ◽  
Passive Flow ◽  
Centrifugal Instability ◽  
Active Flow

The interaction of a rotating conical flow with a solid surface generates a centrifugal instability. This occurs in the flow over the wings of certain types of aircraft at high angles of attack. Efforts at our laboratory have detected such structures using near-surface flow diagnostics, and shown that they can be effectively alleviated using passive flow control near the surface. Their alleviation removes the narrowband spectral peak at the nominal location of vertical fins on these aircraft. This paper explores the substitution of active flow control techniques that remain conformal to the surface and are only powered during high angle of attack operation. The occurrence of the phenomenon and its 15-dB alleviation with geometric fences are shown on a rounded-edge 42-degree swept, cropped delta wing at 25 degrees angle of attack. The feasibility and power requirements for the plasma actuator are estimated in this paper. The generation of counter-rotating vortices using a double dielectric barrier discharge actuator is demonstrated.

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

2021 ◽  
Vol 18 (1) ◽  
Author(s):  
I. Madan ◽  
N. Tajudin ◽  
M. Said ◽  
S. Mat ◽  
N. Othman ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Delta Wing ◽  
Active Flow Control ◽  
Leading Edge ◽  
Control Technique ◽  
Primary Vortex ◽  
Flow Topology ◽  
Main Observation ◽  
Active Flow

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.

Pressure Feedback Active Flow Control of Unsteady Roll Moment on a UCAS Delta Wing

2019 ◽  
Author(s):  
Xiaowei He ◽  
Xuanhong An ◽  
David R. Williams ◽  
Mathieu Le Provost
Keyword(s):  
Flow Control ◽  
Delta Wing ◽  
Active Flow Control ◽  
Roll Moment ◽  
Pressure Feedback ◽  
Active Flow
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