A Method of Characteristics for Steady Three-dimensional Supersonic Flow with Application to Inclined Bodies of Revolution PDF Download
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Author: John V. Rakich
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Book Description
Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.
Author: John V. Rakich
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Book Description
Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.
Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 482
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Book Description
Author: George E. Kaattari
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 28
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Book Description
Author: Arloe W. Mayne (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
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Book Description
Three-dimensional compressible boundary-layer equations are particularized to the windward symmetry plane of a spherically blunted axisymmetric body at incidence under hypersonic conditions. Through the use eddy transport and streamwise intermittency both transitional and fully turbulent boundary layers may be treated. A scheme is presented for determining the outer-edge boundary conditions based on a mass flow balance treatment of the boundary-layer entrainment of the inviscid flow. A finite-difference technique is described for solving the set of partial differential equation governing the boundary-layer flow, and for treating the streamline-swallowing phenomenon.
Author: E. B. Klunker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
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Book Description
A computational technique, called the method of lines, is developed for computing the flow field about conical configurations at incidence in a supersonic flow. The method, which makes use of the self-similarity property, is developed for the nonlinear flow equations. The method has proved to be an efficient and versatile procedure for constructing the numerical solutions to conical flow problems. It has been successful in computing the flow about circular and elliptic cones at conditions where small regions of supersonic cross flow develop and for the conical delta wings where the region of supersonic cross flow is extensive. The calculations made for circular and elliptic cones as well as for the compression side of various conical delta wings are in good agreement with experiment except in regions where viscous effects become important.
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 1054
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Book Description
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: Carl Kaplan
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 252
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages :
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