Supersonic leeward heating of a triangular wing

1990 ◽  
Vol 30 (4) ◽  
pp. 610-615
Author(s):  
V. N. Brazhko ◽  
N. A. Kovaleva ◽  
L. A. Krylova ◽  
G. I. Maikapar
Keyword(s):  
Triangular Wing

Note on the Extension of Evvard’s Method to Wings with Subsonic Leading Edges Moving at Supersonic Speeds

1957 ◽  
Vol 8 (1) ◽  
pp. 87-102 ◽  
Author(s):  
G. J. Hancock
Keyword(s):  
Flat Plate ◽  
Delta Wing ◽  
Leading Edge ◽  
Wing Surface ◽  
List Type ◽  
Pressure Loading ◽  
Supersonic Speed ◽  
Triangular Wing ◽  
Finite Wing ◽  
The Relationship

SummaryEvvard’s technique is applied to the problem of a thin finite wing moving at a supersonic speed when the leading edge is subsonic. It is developed in two methods:—(i) in which the relationship between the pressure loading and the integrals of the downwash over the wing surface is extended as far as possible, and which has to be computed numerically;(ii) in which approximations are made for the upwash velocities in the neighbourhood of the leading edge, resulting in a series of standard integrals for the estimation of the pressure loading.Method (ii) is applied to the pressure loading on a flat plate triangular wing and cropped delta wing, and the application to more general shapes is discussed.

scholarly journals Numerical simulation of hypersonic flow around a triangular wing

2018 ◽  
Vol 19 (1) ◽  
pp. 1-14
Author(s):  
. Pavel Silvestrov ◽  
◽  
Igor A Kryukov ◽  
Boris V. Obnosov ◽  
◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Hypersonic Flow ◽  
Triangular Wing

Effect of counter-rotating vortices on the development of aircraft wakes

2004 ◽  
Vol 108 (1089) ◽  
pp. 585-592 ◽  
Author(s):  
A. Panaras ◽  
S. G. Voutsinas
Keyword(s):  
Near Field ◽  
Small Radius ◽  
Particle Model ◽  
Large Radius ◽  
Two Dimensional ◽  
Vortex System ◽  
Tip Vortices ◽  
Initial Vorticity ◽  
Aircraft Wake ◽  
Triangular Wing

AbstractA two-dimensional vortex particle model is used for studying the development of the vortex wake generated by the wing of an aircraft in the Trefftz plane. Two-dimensional, finite-area vortex structures simulate the initial vorticity distribution at a near-field cross-section of the wing, as provided by either measurements or simulations. The code is used for studying the effect of weak or strong counter-rotating vortices on the development of an aircraft wake. Application in a three-vortex configuration, consisting of the tip and flap vortices, plus a weak negative vorticity sheet lying between them, supports the hypothesis of Graham that the merging of the tip and flap vortices is prevented, because in such an arrangement the counter-rotating vorticity sheet is wrapped around the primary vortices. The present results indicate that even in the far field the tip and flap vortices remain distinct and follow a helical trajectory with large-pitch and small-radius. The code is next applied to the two-vortex system of Savas’s triangular wing, in which the circulation of the flap vortex is comparable to that of the tip. Although a 2D analysis is inappropriate for stability analysis it is still useful for a quick qualitative investigation. Results indicate that the flap and tip vortices follow a helical trajectory with large-pitch but also very large radius. During one period, the flap vortex covers a span wise distance equal to the wing span. Such a flow has not been observed in flight or in laboratory tests. Actually, Ortegaet al, who studied experimentally the triangular wing of O. Savas, found out that before concluding one full spiral, the vortices are literally destroyed (rapid spreading of their vorticity) by an instability mechanism.

Supersonic flow over a triangular wing

1985 ◽  
Vol 26 (3) ◽  
pp. 391-396 ◽  
Author(s):  
G. N. Dudin ◽  
I. I. Lipatov
Keyword(s):  
Supersonic Flow ◽  
Triangular Wing

Note on the Lift of a Triangular Wing at Supersonic Speeds

1948 ◽  
Vol 27 (1-4) ◽  
pp. 49-55 ◽  
Author(s):  
Richard Calvin Roberts
Keyword(s):  
Triangular Wing
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