A Method of Characteristics Computer Program for Three-dimensional Supersonic Internal Flows

A Method of Characteristics Computer Program for Three-dimensional Supersonic Internal Flows PDF

Author: W. C. Armstrong

Publisher:

Published: 1979

Total Pages: 98

ISBN-13:

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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).

A Method of Characteristics Computer Program for Three-Dimensional Supersonic Internal Flows

A Method of Characteristics Computer Program for Three-Dimensional Supersonic Internal Flows PDF

Author:

Publisher:

Published: 1979

Total Pages: 0

ISBN-13:

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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).

A Computer Program for Three-Dimensional Supersonic Flow with Arbitrarily Defined Boundaries

A Computer Program for Three-Dimensional Supersonic Flow with Arbitrarily Defined Boundaries PDF

Author: Brian A. McIntyre

Publisher:

Published: 1972

Total Pages: 182

ISBN-13:

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A production type computer program has been developed, for the CDC-6500 computer, which is capable of solving supersonic flow problems through arbitrarily shaped three-dimensional geometries. Provisions have been made for the inclusion of an arbitrarily shaped three-dimensional centerbody in the flow. The geometry of the contours may be specified by tabular data or by expressing parameters in an analytic equation. A second-order numerical method of characteristics is used to solve the equations of motion for three-dimensional, steady supersonic flow. (Author).

Analysis of Three-dimensional Inviscid Supersonic Flow Between a Body and an Outer Wall

Analysis of Three-dimensional Inviscid Supersonic Flow Between a Body and an Outer Wall PDF

Author: W. C. Armstrong

Publisher:

Published: 1976

Total Pages: 98

ISBN-13:

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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.

A Second-Order Numerical Method of Characteristics for Three-Dimensional Supersonic Flow. Volume 2. Computer Program User's Manual

A Second-Order Numerical Method of Characteristics for Three-Dimensional Supersonic Flow. Volume 2. Computer Program User's Manual PDF

Author:

Publisher:

Published: 1970

Total Pages: 221

ISBN-13:

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A new method of characteristics numerical scheme for three- dimensional steady flow was developed which has second-order accuracy. Heretofore all such schemes for three-dimensional flow have had accuracies less than second-order. A complete numerical algorithm for computing internal supersonic flows of the type encountered in ramjet, scramjet or rocket propulsion systems was developed and programmed for both the IBM 7094 and CDC 6500 computers. The method was tested for order of accuracy using the exact solution for source flow and Prandtl-Meyer flow. The results of these tests verified the second-order accuracy of the scheme. Additional accuracy tests using existing methods for solution of two-dimensional axisymmetric flows showed that the scheme produces accuracies comparable to that of the two-dimensional method of characteristics. The computer program was used to generate the flow field for several three-dimensional nozzle contours and for nonsymmetric flow into an axisymmetric nozzle. These results reveal the complex nature of three- dimensional flows and the general inadequacy of quasi-three-dimensional analyses which neglect crossflow. An operationally convenient computer program was produced. The program has the capability to analyze nonisoenergetic and nonhomentropic flows of a calorically perfect gas or homentropic flows of a real gas in chemical equilibrium. The initial-value surface options include uniform flow, source flow or axisymmetric tabular data. The nozzle boundary options include conical nozzles, axisymmetric contoured nozzles and super-elliptical nozzles.

The Method of Characteristics for Three-dimensional Real-gas Flows

The Method of Characteristics for Three-dimensional Real-gas Flows PDF

Author: Charles R. Strom

Publisher:

Published: 1967

Total Pages: 264

ISBN-13:

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The method of characteristics is formulated for the computation of the supersonic flow of an inviscid, reacting gas over a smooth three-dimensional body. Various methods of constructing networks of bicharacteristic lines are examined from the point of view of numerical stability and accuracy. A new method of forming the network, which consists of projecting forward along streamlines from data points on specified data planes, is found to be most easily adopted to the particular requirements of nonequilibrium chemistry. The general method was coded for the IBM 7090 computer and the program demonstrated for the case of an ideal gas. Calculations were made for the case of an ideal gas. Calculations were made for the flow about a spherical-tip 15 degree half-angle cone at 10 degree angle of attack and a generalized elliptical body at zero incidence. Since the program yields the pressure distribution along specified streamlines, it is straightforward, in principle, to link it to a finite-rate chemistry stream tube program to treat three-dimensional, nonequilibrium flows. (Author).

A Second-Order Numerical Method of Characteristics for Three-Dimensional Supersonic Flow. Volume 1. Theoretical Development and Results

A Second-Order Numerical Method of Characteristics for Three-Dimensional Supersonic Flow. Volume 1. Theoretical Development and Results PDF

Author:

Publisher:

Published: 1969

Total Pages: 230

ISBN-13:

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A new method of characteristics numerical scheme for three-dimensional steady flow has been developed which has second-order accuracy. A complete numerical algorithm for computing internal supersonic flows of the type encountered in ramjet, scramjet or rocket propulsion systems has been developed and programmed for both the IBM 7094 and CDC 6500 computers. The method has been tested for order of accuracy using the exact solution for source flow and Prandtl-Meyer flow. The results of these tests have verified the second-order accuracy of the scheme. Additional accuracy tests using existing methods for solution of two-dimensional axisymmetric flows have shown that the scheme produces accuracies comparable to that of the two-dimensional method of characteristics. The computer program has been used to generate the flow field for several three-dimensional nozzle contours and for nonsymmetric flow into an axisymmetric nozzle. These results reveal the complex natureof three-dimensional flows and the general inadequacy of quasi-three-dimensional analyses which neglect crossflow. An operationally convenient computer program was produced. The program has the capability to analyze nonisoenergetic and nonhomentropic flows of a calorically perfect gas or homentropic flows of a real gas in chemical equilibrium. The initial-value surface options include uniform flow, source flow or axisymmetric tabular data. The nozzle boundary options include conical nozzles, axisymmetric contoured nozzles and super-elliptical nozzles.

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