Analysis of Three-dimensional Inviscid Supersonic Flow Between a Body and an Outer Wall PDF Download
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Author: W. C. Armstrong
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
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Book Description
The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.
Author: W. C. Armstrong
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
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Book Description
The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.
Author: GINO. MORETTI
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
A thorough understanding of the supersonic flow past an arbitrarily shaped body can only be achieved by solving the three-dimensional aerodynamic problem. It is well known that only numerical techniques can be used, because of the nonlinearity of the equations. Nevertheless, in the field of engineering, a quick, panoramic survey of a problem is often much more interesting and useful than the exact solution on one particular case. With this in mind, we attempted the building up of a technique to be used on a small computing machine. Its advantages are: the simplicity of the program, which can be understood and eventually modified by engineers, not specially skilled in programming; a direct control of the results, as far as they are typed out; the choice of different degrees of approximation, including a very rough one, apt for getting a first insight on a given body under several conditions, and seeing how it works. In this report, the essential features of the problem are first examined to obtain suggestions for setting up a technique, and then the numerical procedure which has been set up and programmed is outlined.
Author: Gino Moretti
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 128
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Author: Chong-Wei Chu
Publisher:
ISBN:
Category :
Languages : en
Pages : 205
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Book Description
I ;Powers, Sidney A. ;NOR-72-87-Vol-2F33615-72-C-1429AF-1366AFFDLTR-72-91-Vol-2See also Volume 1, AD-753 695.(*airframes, *supersonic characteristics), (*computer programs, aerodynamics), numerical analysis, conical bodies, delta wings, instruction manuals, blunt bodies, hypersonic characteristics, angle of attack, three dimensional flow, subroutinescomputer aided analysis, smooth bodies, inviscid flowThe report describes the theories, the numerical methods and the computer programs developed for determining the inviscid three-dimensional flow about smooth shapes at supersonic speeds. Volume II is a user's manual for the computer programs and provides the detailed information needed to set up and use the programs. These programs can determine the supersonic flow past smooth blunted bodies for any angle of attack for which the initial value surface remains on the blunted nose. The lowest usable Mach number is on the order of 2.0, with lower values attainable by careful attention to the initial value surface solution. There is no computational upper limit on the Mach number. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Author:
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 148
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Author: John V. Rakich
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Book Description
