A pressure formula for an inclined circular cone in supersonic flow,gamma = 1.4.

AIAA Journal ◽  
1972 ◽  
Vol 10 (2) ◽  
pp. 234-236 ◽  
Author(s):  
D. J. JONES
Keyword(s):  
Supersonic Flow ◽  
Circular Cone

Simple Formulae for Supersonic Flow past a Cone

1975 ◽  
Vol 26 (1) ◽  
pp. 11-19 ◽  
Author(s):  
W H Hui
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Supersonic Flow ◽  
Surface Pressure ◽  
Simple Formula ◽  
Pressure Coefficient ◽  
Circular Cone ◽  
Number Range ◽  
Thin Shock Layer ◽  
Cone Vertex

SummaryThe problem of the supersonic flow with attached shock wave past a circular cone at zero angles of attack is treated, using the thin-shock-layer expansion. The solution is calculated to the fourth approximation. A simple formula is then derived for the surface pressure coefficient by the application of the parameter-straining technique and it is shown to be very accurate for the whole Mach number range for which the shock remains attached to the cone vertex.

Supersonic flow of a vibrationally relaxing gas past a circular cone

1978 ◽  
Vol 85 (3) ◽  
pp. 519-542 ◽  
Author(s):  
James Kao ◽  
J. P. Hodgson
Keyword(s):  
Supersonic Flow ◽  
Numerical Methods ◽  
Numerical Results ◽  
Circular Cone ◽  
Atmospheric Air ◽  
Relaxing Gas ◽  
Characteristic Network

The steady supersonic flow of a vibrationally relaxing gas past a cone is studied using numerical methods. Near the tip of the cone the flow is obtained by means of a coordinate expansion and built on to this is a characteristic network used to obtain the remainder of the flow. Of particular interest is the development of the frozen shock at the tip into a relaxation-dominated wave at distances large compared with the width of the wave. The numerical results are presented in a concise similarity form which will permit accurate extrapolation to very weak waves in atmospheric air.

Supersonic Cone with Surface Blowing

1976 ◽  
Vol 27 (4) ◽  
pp. 243-256 ◽  
Author(s):  
E Carafoli ◽  
C Berbente
Keyword(s):  
Supersonic Flow ◽  
Velocity Field ◽  
Equations Of Motion ◽  
Porous Wall ◽  
Circular Cone ◽  
The Body ◽  
Fluid Injection ◽  
Exact Results ◽  
Practical Applications ◽  
Analytical Formulae

SummaryThe velocity field around a circular cone in supersonic flow is determined by considering fluid injection and suction through the porous wall of the body. By using a new method of linearisation of the equations of motion, analytical formulae are obtained which yield almost exact results, as compared with numerical calculations. In addition, the method proposed suggests new problems related to fluid injection and suction which are important for practical applications.

Aerodynamic Heating of a Thin Sharp-Nose Circular Cone in Supersonic Flow

2005 ◽  
Vol 43 (5) ◽  
pp. 733-745 ◽  
Author(s):  
V. A. Bashkin ◽  
I. V. Egorov ◽  
V. V. Pafnut'ev
Keyword(s):  
Supersonic Flow ◽  
Circular Cone ◽  
Aerodynamic Heating

scholarly journals Nonlinear unsteady supersonic flow analysis for slender bodies of revolution: Series solutions, convergence and results

1998 ◽  
Vol 3 (6) ◽  
pp. 481-501
Author(s):  
M. Markakis ◽  
D. E. Panayotounakos
Keyword(s):  
Supersonic Flow ◽  
Initial Conditions ◽  
Flow Analysis ◽  
Circular Cone ◽  
Series Solutions ◽  
Bodies Of Revolution ◽  
Unsteady Supersonic Flow ◽  
Slender Bodies ◽  
Specific Geometry ◽  
Limiting Values

In Ref. [6] the authors constructed analytical solutions including one arbitrary function for the problem of nonlinear, unsteady, supersonic flow analysis concerning slender bodies of revolution due to small amplitude oscillations. An application describing a flow past a right circular cone was presented and the constructed solutions were given in the form of infinite series through a set of convenient boundary and initial conditions in accordance with the physical problem. In the present paper we develop an appropriate convergence analysis concerning the before mentioned series solutions for the specific geometry of a rigid right circular cone. We succeed in estimating the limiting values of the series producing velocity and acceleration resultants of the problem under consideration. Several graphics for the velocity and acceleration flow fields are presented. We must underline here that the proposed convergence technique is unique and can be applied to any other geometry of the considered body of revolution.

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