Development of a Three-dimensional Supersonic Inlet Flow Analysis PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Development of a Three-dimensional Supersonic Inlet Flow Analysis PDF full book. Access full book title Development of a Three-dimensional Supersonic Inlet Flow Analysis by . Download full books in PDF and EPUB format.
Author:
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 148
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 148
Get Book Here
Book Description
Author: R. C. Buggeln
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 128
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 128
Get Book Here
Book Description
Author: Allan R. Bishop
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Get Book Here
Book Description
A computer program previously developed to analyze three-dimensional supersonic nozzles by the method of characteristics has been modified to study less restrictive nozzle geometries and nonuniform inlet conditions. An example indicates that a one-dimensional calculation that uses an averaged initial profile may be significantly in error. A comparison between the analysis and the data from a three-dimensional experiment shows generally good agreement between the two.
Author: W. C. Armstrong
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
Get Book Here
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: Bernhard H. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Get Book Here
Book Description
Author: T. Kawamura
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
Get Book Here
Book Description
Author: J. M. Solomon
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 236
Get Book Here
Book Description
A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report (Vol. I) the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report (Vol. II User's Manual) contains detailed instructions for operating the code and interpreting the output results. (Author).
Author: Chong-Wei Chu
Publisher:
ISBN:
Category :
Languages : en
Pages : 205
Get Book Here
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: W. C. Armstrong
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
Get Book Here
Book Description
The reference-plane method of characteristics is applied to the computation of the supersonic flow in a three-dimensional (3-D) channel such as a propulsion nozzle. The fluid is assumed to be an inviscid ideal gas and the flow is assumed to be shock-free, although it can be rotational. Both the basic equations and the numerical procedures are described, as is the computer program, which was written in FORTRAN IV language for the IBM 370/165 computer. The validity of the computer program was established by computing, in various ways, an axisymmetric nozzle flow as a three-dimensional flow; the numerical results are in good agreement with the results from a well-established computer program for axisymmetric flow. (Author).
