Flow about Cones at Very High Speeds

1957 ◽  
Vol 8 (4) ◽  
pp. 384-394 ◽  
Author(s):  
H. K. Zienkiewicz
Keyword(s):  
Shock Wave ◽  
High Speed ◽  
Analytic Solution ◽  
Vibrational Excitation ◽  
Circular Cone ◽  
Approximate Analytic Solution ◽  
High Speed Flow ◽  
High Speeds ◽  
Speed Flow ◽  
Very High

Summary:Effects of vibrational excitation and dissociation of air on inviscid high speed flow past a circular cone, at zero incidence, with an attached shock wave, are studied on the assumption of thermal equilibrium. A numerical solution of the problem is outlined and an approximate analytic solution for the flow between the surface of the cone and the shock wave is developed. Two numerical examples are given as an illustration and compared with the corresponding solutions assuming constant air properties.

Boundary Layers and Skin Friction in High-Speed Flow

1951 ◽  
Vol 55 (485) ◽  
pp. 285-302 ◽  
Author(s):  
A. D. Young
Keyword(s):  
Boundary Layer ◽  
Boundary Layers ◽  
High Speed ◽  
Scale Effects ◽  
Practical Interest ◽  
High Speed Flow ◽  
High Speeds ◽  
Speed Flow ◽  
The Subject ◽  
Small Disturbances

SummaryIn this paper an attempt is made to review present knowledge of the subject of boundary layers at high speeds, without delving too deeply into the theory, and to draw attention to the results of practical interest. The introductory remarks describe broadly the special features of boundary layers in compressible flow, namely the existence of both thermal and velocity layers and their interdependence, the sensitivity of the external flow to the layers, and their inter-action with shock waves. The results of importance arising from the theory of the laminar boundary layer and of its stability to small disturbances are then discussed, followed by a summary of the present inadequate state of knowledge of turbulent boundary layer characteristics. It is noted that progress in the latter must await the production of more experimental data. The paper concludes with a discussion of scale effects and the allied problem of boundary layer—shock wave inter-action.

scholarly journals Features of high-speed aircraft numerical simulation

2020 ◽  
Author(s):  
M.M. Alekseeva ◽  
N.A. Brykov ◽  
I.A. Vikhrova
Keyword(s):  
Numerical Simulation ◽  
Gas Dynamics ◽  
High Speed ◽  
Simulation Method ◽  
High Speed Flow ◽  
Flight Tests ◽  
High Speeds ◽  
Physical Experiments ◽  
Speed Flow ◽  
Flow Around A Body

Currently, the creation of new high-speed aircraft is of great interest. The development of such aircraft is associated with the need for experiments and flight tests. The organization of real physical experiments in the field of high speeds is fraught with significant difficulties that can be solved using the numerical simulation method, which makes it possible to significantly simplify the process of creating new products. When developing a high-speed aircraft, it is necessary to take into account the specific aerodynamic and thermophysical features of the processes occurring on the surface of the aircraft and in the shock layer. In this paper, the features of the processes at high speeds are considered on the example of solving the external and internal problems of the gas dynamics of an aircraft. Based on the specifics of these processes, we built a mathematical model that allows us to study the aerodynamics of a high-speed flow around a body in dense layers of the atmosphere and the processes that occur in the combustion chamber.

Critical mach numbers for swept-back wings

1950 ◽  
Vol 2 (2) ◽  
pp. 85-110 ◽  
Author(s):  
S. Neumark
Keyword(s):  
Shock Waves ◽  
High Speed ◽  
Fundamental Problem ◽  
Theoretical Work ◽  
High Speed Flow ◽  
High Speeds ◽  
Speed Flow ◽  
Low Incidence ◽  
The Many ◽  
Work Done

SummaryThe effect of yawing a wing in high-speed flow is to delay the onset of shock waves and to increase the critical Mach number. This is because shock waves can only develop along the isobars (running parallel to the edges of the wing, which is assumed untapered and infinitely long), and therefore only the velocity component normal to the edges is significant. To some extent the same is true for a finite sheared or swept-back wing, though the problem is made more complicated by the various additional factors, such as finite aspect ratio (tip effect), plan form (e.g. taper effect) and, what is perhaps the most important, the central kink effect. The experimental technique is extremely cumbersome because of the many shape parameters involved (see Figs. 1, 2, 3), and since analytical solutions present fundamental difficulties and pitfalls, designers tend to favour rule of thumb methods. The present paper contains a general review of the theoretical work done at The Royal Aircraft Establishment, which was limited to the case of zero incidence. This limitation is not a severe one, as flight at high speeds often implies low incidence. Incidences which are not negligible involve the solution of another fundamental problem (that of the lift distribution).

Visualization of High Speed Flow in a Pipe with Cavity

1997 ◽  
Vol 17 (Supplement2) ◽  
pp. 113-116
Author(s):  
Kenji HOSOI ◽  
Masaaki KAWAHASHI ◽  
Hiroyuki HIRAHARA ◽  
Kouju SHIOZAKI ◽  
Kenichirou SATOH
Keyword(s):  
High Speed ◽  
High Speed Flow ◽  
Speed Flow
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