Supercritical regimes of hypersonic flow past a planar yawed delta wing

1995 ◽  
Vol 30 (4) ◽  
pp. 615-620 ◽  
Author(s):  
G. N. Dudin
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Flow Past

Hypersonic flow past delta wing of finite thickness

1973 ◽  
Vol 5 (3) ◽  
pp. 394-402 ◽  
Author(s):  
A. L. Gonor ◽  
N. A. Ostepenko
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Finite Thickness ◽  
Flow Past

Separated Flow Past a Slender Delta Wing at Incidence

1973 ◽  
Vol 24 (2) ◽  
pp. 120-128 ◽  
Author(s):  
J E Barsby
Keyword(s):  
Delta Wing ◽  
Separated Flow ◽  
Leading Edge ◽  
Vortex Sheet ◽  
Simultaneous Equations ◽  
Delta Wings ◽  
Nested Iteration ◽  
Finite Difference Technique ◽  
Flow Past ◽  
Vortex Systems

SummarySolutions to the problem of separated flow past slender delta wings for moderate values of a suitably defined incidence parameter have been calculated by Smith, using a vortex sheet model. By increasing the accuracy of the finite-difference technique, and by replacing Smith’s original nested iteration procedure, to solve the non-linear simultaneous equations that arise, by a Newton’s method, it is possible to extend the range of the incidence parameter over which solutions can be obtained. Furthermore for sufficiently small values of the incidence parameter, new and unexpected results in the form of vortex systems that originate inboard from the leading edge have been discovered. These new solutions are the only solutions, to the author’s knowledge, of a vortex sheet leaving a smooth surface.Interest has centred upon the shape of the finite vortex sheet, the position of the isolated vortex, and the lift, and variations of these quantities are shown as functions of the incidence parameter. Although no experimental evidence is available, comparisons are made with the simpler Brown and Michael model in which all the vorticity is assumed to be concentrated onto an isolated line vortex. Agreement between these two models becomes very close as the value of the incidence parameter is reduced.

scholarly journals Development of lattice Boltzmann flux solver for simulation of hypersonic flow past flight vehicles

2018 ◽  
Vol 1053 ◽  
pp. 012073
Author(s):  
Zhuxuan Meng ◽  
Liming Yang ◽  
Chang Shu ◽  
Fan Hu ◽  
Donghui Wang ◽  
...  
Keyword(s):  
Hypersonic Flow ◽  
Lattice Boltzmann ◽  
Flight Vehicles ◽  
Flow Past
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