Method of Characteristics for Calculating Three-dimensional Supersonic Gas Flows PDF Download
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Author: Yu N. Podladchikov Publisher: ISBN: Category : Languages : en Pages : 24
Book Description
The method of characteristics (extended from two to three independent variables) is used to solve the problem of supersonic flow of an ideal gas over a blunt body. The steady motion of the gas is described by a system of partial differential equations. A Cartesian coordinate system is fixed to the flow. A scheme based on the relations on the characteristic planes is proposed for calculating the supersonic portion of the flow, and therefore the calculation of a point depends on whether it is found in the shock wave, in the flow field, or on the surface of the body. The computational procedures for these three cases are outlined and illustrated by examples. (Author).
Author: Yu N. Podladchikov Publisher: ISBN: Category : Languages : en Pages : 24
Book Description
The method of characteristics (extended from two to three independent variables) is used to solve the problem of supersonic flow of an ideal gas over a blunt body. The steady motion of the gas is described by a system of partial differential equations. A Cartesian coordinate system is fixed to the flow. A scheme based on the relations on the characteristic planes is proposed for calculating the supersonic portion of the flow, and therefore the calculation of a point depends on whether it is found in the shock wave, in the flow field, or on the surface of the body. The computational procedures for these three cases are outlined and illustrated by examples. (Author).
Author: Charles R. Strom Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 136
Book Description
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).
Author: Z. D. ZAPRYANOV Publisher: ISBN: Category : Languages : en Pages : 10
Book Description
The first section contains a description of the calculation of two-dimensional flows, the second of three-dimensional flows, and the third section contains the results of calculation of flow over a number of specific bodies. The method of characteristics is widely used to calculate supersonic regions of two-dimensional flows.
Author: W. C. Armstrong Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 98
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).
Author: Wolfgang E. Moeckel Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 56
Book Description
Application of the method of characteristics to the linearized three-dimensional equation results in a relatively simple system of difference equations that can be used to compute the supersonic flow past boundaries for which no other linearized solutions are available.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
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).
Author: Yu N. Podladchikov
Author: Yu N. Podladchikov
Author: Charles R. Strom
Author: Z. D. ZAPRYANOV
Author: John V. Rakich
Author: W. C. Armstrong
Author: Chong-Wei Chu
Author: Wolfgang E. Moeckel
Author: 
Author: Chong-Wei Chu
Author: