scholarly journals Aerodynamic Interaction between Delta Wing and Hemisphere-Cylinder in Supersonic Flow

2005 ◽  
Vol 53 (621) ◽  
pp. 446-451 ◽  
Author(s):  
Atsuhiro Nishino ◽  
Takahumi Ishikawa ◽  
Yoshiaki Nakamura
Keyword(s):  
Supersonic Flow ◽  
Delta Wing ◽  
Aerodynamic Interaction

Aerodynamic interaction of two bodies in a supersonic flow

2004 ◽  
Vol 49 (5) ◽  
pp. 315-317 ◽  
Author(s):  
I. A. Zhdan ◽  
V. P. Stulov ◽  
P. V. Stulov
Keyword(s):  
Supersonic Flow ◽  
Aerodynamic Interaction ◽  
Two Bodies

Surface pressures on a wing moving with supersonic speed

1974 ◽  
Vol 341 (1625) ◽  
pp. 177-193 ◽  
Keyword(s):  
Supersonic Flow ◽  
Delta Wing ◽  
Leading Edge ◽  
Ideal Gas ◽  
Numerical Results ◽  
Coordinate Surface ◽  
Supersonic Speed ◽  
Extrapolation Procedure ◽  
Specific Heats ◽  
Limiting Values

Estimates for pressures on the surface of a given delta wing at zero incidence in a steady uniform stream of air are obtained by numerically integrating two semi-characteristic forms of equations which govern the inviscid supersonic flow of an ideal gas with constant specific heats. In one form of the equations coordinate surfaces are fixed in space so that the surface of the wing, which has round sonic leading edges, is a coordinate surface. In the other, two families of coordinates are chosen to be stream-surfaces. For each form of the equations, a finite difference method has been used to compute the supersonic flow around the wing. Convergence of the numerical results, as the mesh is refined, is slow near the leading edge of the wing and an extrapolation procedure is used to predict limiting values for the pressures on the surface of the wing at two stations where theoretical and experimental results have been given earlier by another worker. At one station differences between the results given here and the results given earlier are significant. The two methods used here produce consistent values for the pressures on the surface of the wing and, on the basis of this numerical evidence together with other cited numerical results, it is concluded that the pressures given here are close to the true theoretical values.

On the propagation of weak shock waves

1956 ◽  
Vol 1 (3) ◽  
pp. 290-318 ◽  
Author(s):  
G. B. Whitham
Keyword(s):  
Supersonic Flow ◽  
Delta Wing ◽  
Thickness Distribution ◽  
Leading Edge ◽  
Weak Shock ◽  
Wave Drag ◽  
Main Step ◽  
Body Of Revolution ◽  
Flow Past ◽  
Cone Field

A method is presented for treating problems of the propagation and ultimate decay of the shocks produced by explosions and by bodies in supersonic flight. The theory is restricted to weak shocks, but is of quite general application within that limitation. In the author's earlier work on this subject (Whitham 1952), only problems having directional symmetry were considered; thus, steady supersonic flow past an axisymmetrical body was a typical example. The present paper extends the method to problems lacking such symmetry. The main step required in the extension is described in the introduction and the general theory is completed in §2; the remainder of the paper is devoted to applications of the theory in specific cases.First, in §3, the problem of the outward propagation of spherical shocks is reconsidered since it provides the simplest illustration of the ideas developed in §2. Then, in §4, the theory is applied to a model of an unsymmetrical explosion. In §5, a brief outline is given of the theory developed by Rao (1956) for the application to a supersonic projectile moving with varying speed and direction. Examples of steady supersonic flow past unsymmetrical bodies are discussed in §6 and 7. The first is the flow past a flat plate delta wing at small incidence to the stream, with leading edges swept inside the Mach cone; the results agree with those previously found by Lighthill (1949) in his work on shocks in cone field problems, and this provides a valuable check on the theory. The second application in steady supersonic flow is to the problem of a thin wing having a finite curved leading edge. It is found that in any given direction the shock from the leading edge ultimately decays exactly as for the bow shock on a body of revolution; the equivalent body of revolution for any direction is determined in terms of the thickness distribution of the wing and varies with the direction chosen. Finally in §8, the wave drag on the wing is calculated from the rate of dissipation of energy by the shocks. The drag is found to be the mean of the drags on the equivalent bodies of revolution for the different directions.

Boundary layer transition on the surface of a delta wing in supersonic flow

1989 ◽  
Vol 24 (3) ◽  
pp. 398-402
Author(s):  
V. N. Brazhko ◽  
N. A. Kovaleva ◽  
L. A. Krylova ◽  
G. I. Maikapar
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Delta Wing ◽  
Boundary Layer Transition ◽  
Layer Transition

Vortical structures of supersonic flow over a delta-wing on a flat plate

2013 ◽  
Vol 102 (6) ◽  
pp. 061911 ◽  
Author(s):  
D. P. Wang ◽  
Z. X. Xia ◽  
Y. X. Zhao ◽  
Q. H. Wang ◽  
B. Liu
Keyword(s):  
Supersonic Flow ◽  
Flat Plate ◽  
Delta Wing ◽  
Vortical Structures
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