Author: Jon AhnPublisher:
ISBN:
Category :
Languages : en
Pages : 94
Book Description
Analysis and Design of Axisymmetric Transonic Flow with Linearized Three-dimensional Flow Prediction
Author: Jon AhnNewton Method on Axisymmetric Transonic Flow and Linearized 3-D Flow Prediction
Author: Jon AhnThree-Dimensional Transonic Flow Analysis
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
A computer program was written to calculate the steady, inviscid, transonic flow about an unyawed wing/body configuration. The code is based on the nonconservative form of the full potential equation formulated in global, wing-adapted coordinates that are not surface-conforming. Numerical solution of the governing equations is accomplished via application of type-dependent, rotated finite-difference operators and the method of line relaxation. Exact wing/body surface conditions are enforced by an imaging scheme that involves both surface control points and surface-adjacent computation points. Coordinate stretching permits far-field boundary conditions to be treated exactly; an embedded relaxation scheme computes the downwash field in the Trefftz plane. Present geometric capability includes a quite general wing attached at mid-height to a blunt-nosed, semi-infinite cylinder of varying crossplane radius. Representative solutions computed on a grid of moderate density are presented for a checkout configuration that includes ONERA Wing M6; comparisons with wing-alone experimental data are shown also. Code limitations and modifications required to further develop the program are discussed. A code listing and a user's guide summary are provided. (Author).
Scientific and Technical Aerospace Reports
Author: American Doctoral Dissertations
Author: Publisher:
ISBN:
Category : Dissertation abstracts
Languages : en
Pages : 784
Book Description
Transonic, Shock, and Multidimensional Flows
Author: Richard E. MeyerPublisher: Academic Press
ISBN: 1483264602
Category : Technology & Engineering
Languages : en
Pages : 356
Book Description
Mathematics Research Center Symposium: Transonic, Shock, and Multidimensional Flows: Advances in Scientific Computing covers the lectures presented at a Symposium on Transonic, Shock, and Multidimensional Flows, held in Madison on May 13-15, 1981, under the auspices of the Mathematics Research Center of the University of Wisconsin. The book focuses on the advancements in the scientific computation of high-speed aerodynamic phenomena and related fluid motions. The selection first elaborates on computational fluid dynamics of airfoils and wings; shock-free configurations in two- and three-dimensional transonic flow; and steady-state solution of the Euler equations for transonic flow. Discussions focus on boundary conditions, convergence acceleration, indirect design of airfoils, and trailing edge and the boundary layer. The text then examines the calculation of transonic potential flow past three-dimensional configurations and remarks on the numerical solution of Tricomi-type equations. The manuscript ponders on the design and numerical analysis of vortex methods, shock calculations and the numerical solution of singular perturbation problems, tracking of interfaces for fluid flow, and transonic flows with viscous effects. Topics include numerical algorithm, difference approximation for scalar equations, boundary conditions, transonic flow in a tube, and governing equations. The selection is a dependable reference for researchers interested in transonic, shock, and multidimensional flows.
Aeronautical Engineering
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Three-Dimensional Transonic Flow Analysis
Author: Gerald E. ChmielewskiPublisher:
ISBN:
Category :
Languages : en
Pages : 97
Book Description
A computer program was written to calculate the steady, inviscid, transonic flow about an unyawed wing/body configuration. The code is based on the nonconservative form of the full potential equation formulated in global, wing-adapted coordinates that are not surface-conforming. Numerical solution of the governing equations is accomplished via application of type-dependent, rotated finite-difference operators and the method of line relaxation. Exact wing/body surface conditions are enforced by an imaging scheme that involves both surface control points and surface-adjacent computation points. Coordinate stretching permits far-field boundary conditions to be treated exactly; an embedded relaxation scheme computes the downwash field in the Trefftz plane. Present geometric capability includes a quite general wing attached at mid-height to a blunt-nosed, semi-infinite cylinder of varying crossplane radius. Representative solutions computed on a grid of moderate density are presented for a checkout configuration that includes ONERA Wing M6; comparisons with wing-alone experimental data are shown also. Code limitations and modifications required to further develop the program are discussed. A code listing and a user's guide summary are provided. (Author).
Author: 
Author: