Second-order Small-disturbance Solutions for Hypersonic Flow Over Power-law Bodies PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Second-order Small-disturbance Solutions for Hypersonic Flow Over Power-law Bodies PDF full book. Access full book title Second-order Small-disturbance Solutions for Hypersonic Flow Over Power-law Bodies by James Courtland Townsend. Download full books in PDF and EPUB format.
Author: James Courtland Townsend
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
Get Book Here
Book Description
Author: James Courtland Townsend
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
Get Book Here
Book Description
Author: Harold Mirels
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
Get Book Here
Book Description
Approximate analytical solutions are presented for two-dimensional and axisymmetric hypersonic flow over slender power law bodies. Both zero-order (M->∞) and first-order (small but nonvanishing values of 1/(Mδ)2) solutions are presented, where M is free-stream Mach number and δ is a characteristic slope. These solutions are compared with exact numerical integrations of the equations of motion and appear to be accurate particularly when the shock is relatively close to the body.
Author: Harold Mirels
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 244
Get Book Here
Book Description
Author: J. J. Chattot
Publisher: Springer
ISBN: 9401798257
Category : Science
Languages : en
Pages : 625
Get Book Here
Book Description
This book covers classical and modern aerodynamics, theories and related numerical methods, for senior and first-year graduate engineering students, including: -The classical potential (incompressible) flow theories for low speed aerodynamics of thin airfoils and high and low aspect ratio wings. - The linearized theories for compressible subsonic and supersonic aerodynamics. - The nonlinear transonic small disturbance potential flow theory, including supercritical wing sections, the extended transonic area rule with lift effect, transonic lifting line and swept or oblique wings to minimize wave drag. Unsteady flow is also briefly discussed. Numerical simulations based on relaxation mixed-finite difference methods are presented and explained. - Boundary layer theory for all Mach number regimes and viscous/inviscid interaction procedures used in practical aerodynamics calculations. There are also four chapters covering special topics, including wind turbines and propellers, airplane design, flow analogies and hypersonic (rotational) flows. A unique feature of the book is its ten self-tests and their solutions as well as an appendix on special techniques of functions of complex variables, method of characteristics and conservation laws and shock waves. The book is the culmination of two courses taught every year by the two authors for the last two decades to seniors and first-year graduate students of aerospace engineering at UC Davis.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 796
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1932
Get Book Here
Book Description
Author: Harold Mirels
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Get Book Here
Book Description
Self-similar flows with volumetric mass, momentum, and energy addition are investigated. Unsteady flows bounded by shock waves and equivalent steady hypersonic flows over slender bodies are considered, and the form of the shock shape and of the volumetric sources for self-similar motion are noted. For unsteady flows, it is found that the shock shape mu t have the form R sub O=ct to the m power (where R sub O = shock ordinate, t = time) and that the mass, momentum, and energ sources must be expressible in the fom of a funtion of r/R sub O times t to the -1 power, t to the m-2 power, and t to the 2m-3 power, respectively (where r is the lateral ordinate). If the sources introduce only sll perturbations in an otherwise self-similar flow, solutions can be obtained for sources expressible as a function of r/R sub O times t to arbitrary constant exponents. Thus, the small perturbation case is less restrictive with regard to the functional form of the sources. For equivalent steady hypersonic flows, the streamwise distance, x, replaces t in the above expressions. Numerical perturbation solutions are obtained for the effect of a uniform transverse magnetic field on piston-driven flows and blast waves. The firstorder effect of body-thickness raio on the hypersonic flow (in the limit of infinite Mach number) over slender power law bodies is aso reated. (Author).
Author: John David Anderson
Publisher: AIAA
ISBN: 9781563474590
Category : Science
Languages : en
Pages : 710
Get Book Here
Book Description
This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
