The Wave Drag of Blunted Cones in Axisymmetric Supersonic Flow

2003 ◽  
Author(s):  
Paul Eremenko ◽  
Christopher Mouton ◽  
Hans Hornung
Keyword(s):  
Supersonic Flow ◽  
Wave Drag ◽  
Axisymmetric Supersonic Flow

Base heat transfer in an axisymmetric supersonic flow

AIAA Journal ◽  
1970 ◽  
Vol 8 (5) ◽  
pp. 974-976 ◽  
Author(s):  
LEROY S. FLETCHER
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Axisymmetric Supersonic Flow

The Quasi-Cylinder of Specified Thickness and Shell Loading in Supersonic Flow

1960 ◽  
Vol 11 (4) ◽  
pp. 387-395
Author(s):  
H. Portnoy
Keyword(s):  
Supersonic Flow ◽  
Shell Thickness ◽  
Operational Calculus ◽  
Wave Drag ◽  
Small Disturbance ◽  
Characteristic Cone ◽  
Present Solution ◽  
The Mean ◽  
Disturbance Field ◽  
General Method

SummaryThe methods of the operational calculus are used to obtain a linear approximation to the shape of the mean camber surface of a quasi-cylinder in a supersonic flow in terms of its shell thickness and loading distributions. The analysis deals with a generalised quasi-cylinder; that is one which, although lying close to a mean cylinder, need not possess axial symmetry. The quasi-cylinder is also permitted to be within the small disturbance field of other separate components, e.g. a centre-body. Because the linearised theory is inadmissable for internal duct flows close to and beyond the first reflected characteristic cone, the present solution is likewise invalid close to and beyond the position where this characteristic meets the mean cylinder. The work given here enables the camber shapes of “ring-wings”, which have been used theoretically to reduce or even nullify the wave-drag of a central slender-body, to be found. An example illustrates the general method.

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.

The Drag of Non-Planar Thickness Distributions in Supersonic Flow

1955 ◽  
Vol 6 (2) ◽  
pp. 99-113 ◽  
Author(s):  
E. W. Graham ◽  
B. J. Beane ◽  
R. M. Licher
Keyword(s):  
Supersonic Flow ◽  
Thickness Distribution ◽  
Wave Drag ◽  
Body Of Revolution ◽  
Optimum Distribution ◽  
Planar Source

SummaryFor many conventional aircraft, the thickness of the wing and fuselage can be represented approximately by source distributions in the plane of the wing and on the axis of the fuselage. Such aircraft may be considered as having essentially planar thickness distributions. However, missiles with cruciform wings, biplane arrangements, “ ring ” wings and so on, require non-planar source distributions to represent the wing and fuselage thickness. For this reason, the term “ spatial thickness distribution ” is used.To simplify the investigation of spatial thickness distributions, a singularity representing an element of volume is introduced. It is shown that the optimum distribution of such elements in a prescribed space gives rise to a minimum wave drag value consistent with that obtained for a Sears- Haack optimum body of revolution.

Effect of mesh screens on the wave drag of a blunt body in supersonic flow

2012 ◽  
Vol 19 (2) ◽  
pp. 201-208 ◽  
Author(s):  
S. G. Mironov ◽  
K. M. Serdyuk
Keyword(s):  
Supersonic Flow ◽  
Blunt Body ◽  
Wave Drag
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