Dynamic characteristics of axially symmetric supersonic flow under microwave conditions

2003 ◽  
Author(s):  
Zhao Qingxun ◽  
Ding Wenge ◽  
Zhang Kaixi
Keyword(s):  
Supersonic Flow ◽  
Dynamic Characteristics ◽  
Axially Symmetric

Calculation of Supersonic Flow Past an Axially Symmetric Cylinder

1958 ◽  
Vol 25 (4) ◽  
pp. 269-270 ◽  
Author(s):  
Martha W. Evans ◽  
Francis H. Harlow
Keyword(s):  
Supersonic Flow ◽  
Axially Symmetric ◽  
Flow Past

The Supersonic Flow Past an Elliptic Cone

1969 ◽  
Vol 20 (4) ◽  
pp. 382-404 ◽  
Author(s):  
B. A. Woods
Keyword(s):  
Supersonic Flow ◽  
Axially Symmetric ◽  
Conical Flow ◽  
Small Eccentricity ◽  
First Order ◽  
Flow Past ◽  
Elliptic Cone ◽  
Large Eccentricity ◽  
Cone Surface ◽  
Valid Solution

SummaryThe supersonic flow past an elliptic cone of small eccentricity is treated as a pertubation of the axially-symmetric conical flow. The perturbation is singular; a uniformly valid solution is constructed by formulating the problem in sphero-conal coordinates (in which the cone surface is always a level surface of one of the coordinates) and by using the method of matched asymptotic expansions. This formulation enables first-order results to be obtained economically. In a numerical example for the flow past a cone of quite large eccentricity at incidence, it is shown that the present first-order solution (of three terms) agrees as well with experiment as a ten-term approximation obtained by Martellucci using the method of linearised characteristics.

XXVII.—The Rotational Field behind a Bow Shock Wave in Axially Symmetric Flow using Relaxation Methods

1952 ◽  
Vol 63 (4) ◽  
pp. 371-380
Author(s):  
A. R. Mitchell ◽  
Francis McCall
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Supersonic Flow ◽  
Bow Shock ◽  
Axially Symmetric ◽  
Relaxation Methods ◽  
Bow Shock Wave ◽  
Constant Vorticity ◽  
Complete Field ◽  
Rotational Field

SynopsisThe relaxation technique of R. V. Southwell is developed to evaluate mixed subsonic-supersonic flow regions with axial symmetry, changes of entropy being taken into account. In the problem of a parallel supersonic flow of Mach number I·8 impinging on a blunt-nosed axially symmetric obstacle, the new technique is used to determine the complete field downstream of the bow shock wave formed. Lines of constant vorticity and Mach number are shown in the field, and where possible a comparison is made with the corresponding 2-dimensional problem.

Cowl Shapes of Minimum Drag in Supersonic Flow

1965 ◽  
Vol 69 (650) ◽  
pp. 121-126
Author(s):  
E. Angus Boyd
Keyword(s):  
Supersonic Flow ◽  
Diameter Ratio ◽  
Computer Method ◽  
Impact Pressure ◽  
Axially Symmetric ◽  
Flow Equations ◽  
Minimum Pressure ◽  
Pressure Drag ◽  
General Flow ◽  
Minimum Drag

In part 1 of this paper the shape of an axially symmetric ducted body, of given length and fineness ratio, having minimum pressure drag was derived using the Newtonian impact pressure law. It was shown that this shape closely approximated that found by a computer method of Guderley, Armitage and Valentine which employed the general flow equations. Indeed the two curves could be distinguished only for values of the diameter ratio Δ=di/df, of the initial and final diameters, so small as to be outside the range likely to be used for cowl shapes.

The supersonic flow of compressible fluid through axially symmetric tubes of uniform and varying section

1950 ◽  
Vol 200 (1063) ◽  
pp. 511-523
Keyword(s):  
Supersonic Flow ◽  
Velocity Field ◽  
Power Series ◽  
Wide Class ◽  
Compressible Fluid ◽  
Inviscid Fluid ◽  
Nozzle Wall ◽  
Axially Symmetric ◽  
Rates Of Change ◽  
Rotational Flows

The paper considers potentials representing the supersonic flow of a compressible, inviscid fluid in axially symmetric tubes or diffusers. General formulae are given to determine the linearized flows completely when the inlet distributions of velocity are known, in cases where the slope of the nozzle wall is continuous, and where there are no discontinuities in the velocity field or in the rates of change of velocity. Particular reference is made to the flows resulting from velocity distributions which are initially parabolic. Formulae are given to enable the computer to tabulate a very wide class of axisymmetric flows, mention being made of the propagation of other profiles which are non-parabolic. A further method is given for extending the field by use of power series approximation. A discussion of rotational flows in divergent diffusers will be given in a later paper.

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