Numerical Investigation of Reynolds Number Effects on a Blunt Leading-Edge Delta Wing

2006 ◽  
Author(s):  
Simone Crippa ◽  
Arthur Rizzi
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Delta Wing ◽  
Leading Edge ◽  
Reynolds Number Effects ◽  
Blunt Leading Edge

Effects of leading-edge bevel angle on the aerodynamic forces of a non-slender 50° delta wing

2005 ◽  
Vol 109 (1098) ◽  
pp. 403-407 ◽  
Author(s):  
J. J. Wang ◽  
S. F. Lu
Keyword(s):  
Delta Wing ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Relative Thickness ◽  
Aerodynamic Performances ◽  
Stall Angle ◽  
Drag Ratio ◽  
Low Speed Wind Tunnel ◽  
Lift To Drag Ratio ◽  
Blunt Leading Edge

Abstract The aerodynamic performances of a non-slender 50° delta wing with various leading-edge bevels were measured in a low speed wind tunnel. It is found that the delta wing with leading-edge bevelled leeward can improve the maximum lift coefficient and maximum lift to drag ratio, and the stall angle of the wing is also delayed. In comparison with the blunt leading-edge wing, the increment of maximum lift to drag ratio is 200%, 98% and 100% for the wings with relative thickness t/c = 2%, t/c = 6.7% and t/c = 10%, respectively.

Reynolds Number Effects on Flow Topology Above Blunt-edged Delta Wing VFE-2 Configurations

2015 ◽  
Author(s):  
Mazuriah Said ◽  
Shabudin B. Mat ◽  
Shuhaimi Mansor ◽  
Ainullotfi Abdul-Latif ◽  
Tholudin Mat Lazim
Keyword(s):  
Reynolds Number ◽  
Delta Wing ◽  
Flow Topology ◽  
Reynolds Number Effects

Numerical investigation of Reynolds number effects on vortex-induced vibrations at low and moderate Re regimes

2022 ◽  
Vol 245 ◽  
pp. 110535
Author(s):  
Jian Gu ◽  
Antonio Carlos Fernandes ◽  
Xiangxi Han ◽  
Xiaofeng Kuang ◽  
Wei Chen
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Vortex Induced Vibrations ◽  
Reynolds Number Effects

scholarly journals Numerical Investigation on the Reynolds Number Effects of Supercritical Airfoil

2012 ◽  
Vol 31 ◽  
pp. 103-109 ◽  
Author(s):  
Dawei Liu ◽  
Yuanjing Wang ◽  
Dehua Chen ◽  
Xin Peng ◽  
Xing Xu
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Supercritical Airfoil ◽  
Reynolds Number Effects

scholarly journals Laminar-turbulent transition in the vicinity of blunt leading edge of flat delta wing in hypersonic flow

2017 ◽  
Author(s):  
A. V. Vaganov ◽  
D. V. Grachikov ◽  
V. M. Kashin ◽  
V. D. Nemykin ◽  
A. Yu. Noev ◽  
...  
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Leading Edge ◽  
Turbulent Transition ◽  
Blunt Leading Edge ◽  
Laminar Turbulent Transition

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.

Numerical Investigation of the Effect of Leading Edge Tubercles at Low Reynolds Number

2018 ◽  
Author(s):  
V. T. Gopinathan ◽  
J. Bruce Ralphin Rose ◽  
V. Gokul ◽  
K. Kamalahasan
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Low Reynolds Number ◽  
Leading Edge ◽  
Low Reynolds

Numerical Investigation on the Reynolds Number Effects of Supercritical Wing

2014 ◽  
Author(s):  
Dawei Liu ◽  
Xin Xu ◽  
Qiang Li ◽  
Mingjie Jiang ◽  
Xin Peng
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Reynolds Number Effects
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