THE BLUNT-LEADING-EDGE PROBLEM IN HYPERSONIC FLOW

AIAA Journal ◽  
1963 ◽  
Vol 1 (2) ◽  
pp. 361-368 ◽  
Author(s):  
HAKURO OGUCHI
Keyword(s):  
Hypersonic Flow ◽  
Leading Edge ◽  
Edge Problem ◽  
Blunt Leading Edge

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

INFLUENCE OF THE PLATE LEADING-EDGE SHAPE AND THICKNESS ON THE BOUNDARY LAYER LAMINAR-TURBULENT TRANSITION IN HYPERSONIC FLOW

2019 ◽  
Vol 50 (5) ◽  
pp. 461-481
Author(s):  
Sergei Vasilyevich Aleksandrov ◽  
Evgeniya Andreevna Aleksandrova ◽  
Volf Ya. Borovoy ◽  
Andrey Vyacheslavovich Gubernatenko ◽  
Vladimir Evguenyevich Mosharov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Hypersonic Flow ◽  
Leading Edge ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

scholarly journals Smooth leading edge transition in hypersonic flow

1999 ◽  
Vol 26 (1-2) ◽  
pp. 169-176 ◽  
Author(s):  
L. Gaillard ◽  
E. Benard ◽  
T. Alziary de Roquefort
Keyword(s):  
Hypersonic Flow ◽  
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.

Three-dimensional shock interactions and vortices on a V-shaped blunt leading edge

2019 ◽  
Vol 31 (8) ◽  
pp. 086102 ◽  
Author(s):  
Enlai Zhang ◽  
Zhufei Li ◽  
Yiming Li ◽  
Jiming Yang
Keyword(s):  
Three Dimensional ◽  
Leading Edge ◽  
Shock Interactions ◽  
Blunt Leading Edge
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