Aeroelastic Response of a Delta Wing at High Angles of Attack

2003 ◽  
Author(s):  
Raymond Gordnier ◽  
Miguel Visbal
Keyword(s):  
Delta Wing ◽  
Aeroelastic Response ◽  
High Angles Of Attack

Aerodynamic characteristics of delta wing–body combinations at high angles of attack

1994 ◽  
Vol 98 (975) ◽  
pp. 159-170 ◽  
Author(s):  
P. R. Viswanath ◽  
S. R. Patil
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Aerodynamic Characteristics ◽  
Surface Flow ◽  
Flow Visualisation ◽  
Symmetric Flow ◽  
Gradual Process ◽  
Wing Sweep ◽  
The Mean ◽  
High Angles Of Attack

AbstractAn experimental study investigating the aerodynamic characteristics of generic delta wing-body combinations up to high angles of attack was carried out at a subsonic Mach number. Three delta wings having sharp leading edges and sweep angles of 50°, 60° and 70° were tested with two forebody configurations providing a variation of the nose fineness ratio. Measurements made included six-component forces and moments, limited static pressures on the wing lee-side and surface flow visualisation studies. The results showed symmetric flow features up to an incidence of about 25°, beyond which significant asymmetry was evident due to wing vortex breakdown, forebody vortex asymmetry or both. At higher incidence, varying degrees of forebody-wing vortex interaction effects were seen in the mean loads, which depended on the wing sweep and the nose fineness ratio. The vortex breakdown on these wings was found to be a gradual process, as implied by the wing pressures and the mean aerodynamic loads. Effects of forebody vortex asymmetry on the wing-body aerodynamics have also been assessed. Comparison of Datcom estimates with experimental data of longitudinal aerodynamic characteristics on all three wing-body combinations indicated good agreement in the symmetric flow regime.

Plasma Control of Vortex Flow on Delta-Wing at High Angles of Attack

2009 ◽  
Author(s):  
Andrey Sidorenko ◽  
Alexey Budovsky ◽  
Boris Postnikov ◽  
Boris Zanin ◽  
Ilya Zverkov ◽  
...  
Keyword(s):  
Vortex Flow ◽  
Delta Wing ◽  
High Angles Of Attack ◽  
Plasma Control

Vortical flows over a LEX-delta wing at high angles of attack

2004 ◽  
Vol 18 (12) ◽  
pp. 2273-2283 ◽  
Author(s):  
Young-Ki Lee ◽  
Heuy-Dong Kim
Keyword(s):  
Delta Wing ◽  
Vortical Flows ◽  
High Angles Of Attack

Plasma control of vortex flow on a delta wing at high angles of attack

2013 ◽  
Vol 54 (8) ◽  
Author(s):  
Andrey A. Sidorenko ◽  
Alexey D. Budovskiy ◽  
Anatoly A. Maslov ◽  
Boris V. Postnikov ◽  
Boris Yu. Zanin ◽  
...  
Keyword(s):  
Vortex Flow ◽  
Delta Wing ◽  
High Angles Of Attack ◽  
Plasma Control

Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks

2020 ◽  
Vol 17 (3) ◽  
pp. 8214-8223
Author(s):  
M. Said ◽  
M. Imai ◽  
S. Mat ◽  
M. N. Dahalan ◽  
S. Mansor ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Surface Pressure ◽  
Delta Wing ◽  
Measurement Techniques ◽  
Initial Point ◽  
Leading Edge ◽  
Flow Visualisation ◽  
Pressure Measurements ◽  
Wing Model ◽  
High Angles Of Attack

This paper reports on flow visualisation and surface pressure measurements over the upper surface of a blunt-edged delta wing model at high angles of attack. The flow structure above the upper surface of the blunt-edged delta wing was found to be different compared to delta wing with sharp leading edge. The flow becomes more complicated especially in the leading edge region of the wing. Currently, there is no data available to verify if the primary vortex could reach the apex of the wing when the angle of attack is further increased. Most prior experiments were performed at the angles of attack, α, below 23° with only a few experiments that had gone to α = 27°. These prior experiments and some CFD works stipulated that the attached flow continue to exist in the apex region of the delta wing even at very high angles of attack above 23°. In order to verify this hypothesis, several experiments at high angles of attack were conducted in Universiti Teknologi Malaysia Low Speed wind Tunnel (UTM–LST), using a specially constructed VFE2 wing model equipped with blunt leading edges. This series of experiments employed two measurement techniques; the first was the long tuft flow visualisation method, followed by surface pressure measurements. The experiments were performed at Reynolds numbers of 1.0×106 and 1.5×106.  During these experiments, several interesting flow characteristics were observed at high angles of attack, mainly that the flow became more sensitive to changes in Reynolds number and the angles of attack of the wing. When the Reynolds number increased from 1×106 to 1.5×106, the upstream progression of the initial point of the main vortex was relatively delayed compared to the sharp-edged delta wing. The experiments also showed that the flow continued to be attached in the apex region up to α = 27º.

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