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Author: Gerald E. Chmielewski Publisher: 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: Gerald E. Chmielewski Publisher: 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: 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).
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722915001 Category : Languages : en Pages : 28
Book Description
A new method is presented for calculating the quasi-steady transonic flow over a lifting or non-lifting rotor blade in both hover and forward flight by using Euler equations. The approach is to solve Euler equations in a rotor-fixed frame of reference using a finite volume method. A computer program was developed and was then verified by comparison with wind-tunnel data. In all cases considered, good agreement was found with published experimental data. Chang, I-Chung Ames Research Center RTOP 505-61-51...
Author: Richard A. Weed Publisher: ISBN: Category : Languages : en Pages : 60
Book Description
This users guide describes the input and operation requirements of a computer code for the analysis and design of wings in transonic flow. A synopsis of the function of the major subroutines in the program is given in addition to a detailed description of the input variables required to run the code. Sample data sets are presented that illustrate the data sequence required for various code options. Keywords: Transonic flow analysis; Inverse wing design; Computational aerodynamics; Finite differences.
Author: Gerald E. Chmielewski
Author: Gerald E. Chmielewski
Author: 
Author: I-Chung Chang
Author: National Aeronautics and Space Administration (NASA)
Author: 
Author: I-Chung Chang
Author: I. C. Chang
Author: Antoine Bourgeade
Author: Jon Ahn
Author: Richard A. Weed