Stationary flow past the lower surface of a piecewise planar delta wing with supersonic leading edges

1979 ◽  
Vol 14 (5) ◽  
pp. 699-708
Author(s):  
S. M. Ter-Minasyants
Keyword(s):  
Delta Wing ◽  
Stationary Flow ◽  
Lower Surface ◽  
Flow Past ◽  
Leading Edges

The Flow Past a Delta-Wing-Half-Cone Combination with Subsonic Leading Edges

1964 ◽  
Vol 15 (4) ◽  
pp. 311-327 ◽  
Author(s):  
H. Portnoy
Keyword(s):  
Delta Wing ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Conical Flows ◽  
Flow Past ◽  
Edge Loading ◽  
Attached Flow ◽  
The Common ◽  
Leading Edges ◽  
Half Cone

SummaryThe flow past an unyawed, flat, delta wing with subsonic edges, carrying a slender half-cone mounted centrally underneath, is found by using the method of supersonic conical flows. The wing plane is taken to be at zero incidence, but it is shown that wing incidence, camber, twist and thickness effects may be incorporated by superimposing on this solution the field of the isolated wing with these properties. The results are shown to agree with previous work on configurations with sonic or supersonic leading edges for the common case of sonic edges. The leading edge loading may be made zero to secure attached flow at any lift coefficient by using camber and incidence, but it is shown that there is a certain positive lift coefficient for which a negative incidence alone will suffice.

The Shock Pattern of a Wing-Body Combination, Far from the Flight Path

1958 ◽  
Vol 9 (2) ◽  
pp. 164-194 ◽  
Author(s):  
F. Walkden
Keyword(s):  
Shock Wave ◽  
Unsteady Flow ◽  
Linear Theory ◽  
Delta Wing ◽  
Flight Path ◽  
The Body ◽  
Body Of Revolution ◽  
Flow Past ◽  
Leading Edges

SummaryThe position and strength of the front shock wave at large distances from a wing-body combination, are deduced from the linear theory for the combination, using a method developed by Whitham. The combination consists of a body of revolution and a wing which has thickness and is lifting. The effects of interference between the flow over the body and the flow over the wing are included. In any direction the flow far from the wing-body combination is equivalent to the flow past a body of revolution determined from the configuration of the combination. The modified formulae for unsteady flow are given and some results are evaluated for the combination of a body of revolution and a delta wing with subsonic leading edges.

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.

On the Effect of the Incident Mach’s Wave on the Pulsation Level in Boundary Layer of the Plane Delta Wing

2014 ◽  
Vol 9 (1) ◽  
pp. 29-38
Author(s):  
Aleksandr Vaganov ◽  
Yuri Yermolaev ◽  
Gleb Kolosov ◽  
Aleksandr Kosinov ◽  
Aleksandra Panina ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mass Flow ◽  
Delta Wing ◽  
Level Fluctuation ◽  
Flow Pulsation ◽  
Flow Conditions ◽  
Wing Model ◽  
Maximum Value ◽  
Leading Edges ◽  
High Level

The experimental results of high level fluctuation excitation by external Mach’s wave in the boundary layer of delta wing model with blunt leading edges at Mach numbers M = 2, 2.5, 4 are presented. The exitation areas and mass flow pulsation levels in the conditions of subsonic, sonic and supersonic leading edges have been defined. It was found that the maximum value of the pulsations is 12–15 % and varies only slightly from the flow conditions around of the delta wing

Vortex flow and lift generation of a non-slender reverse delta wing

2016 ◽  
Vol 231 (13) ◽  
pp. 2438-2451
Author(s):  
T Lee ◽  
LS Ko
Keyword(s):  
Particle Image Velocimetry ◽  
Lift Force ◽  
Vortex Flow ◽  
Particle Image ◽  
Delta Wing ◽  
Lower Surface ◽  
Force Balance ◽  
Flow Parameters ◽  
Image Velocimetry ◽  
Spanwise Vortex

The vortex flow and lift force generated by a 50°-sweep non-slender reverse delta wing were investigated via particle image velocimetry, together with flow visualization and force balance measurement, at Re = 11,000. The non-slender reverse delta wing produced a delayed stall but a lower lift compared to its delta wing counterpart. The stalling mechanism was also found to be triggered by the disruption of the multiple spanwise vortex filaments developed over the upper wing surface. The vortex flowfield was, however, characterized by the co-existence of reverse delta wing vortices and multiple shear-layer vortices. The outboard location of the reverse delta wing vortex further implies that the lift force is mainly generated by the wing lower surface while the upper surface acts as a wake generator. The spatial progression of the flow parameters of the vortex generated by the non-slender reverse delta wing as a function of α was also discussed.

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