The Expansion of a Supersonic, Laminar Boundary Layer Around a Convex Corner
Author : James W. Gress
Publisher :
Page : 82 pages
File Size : 27,60 MB
Release : 1968
Category :
ISBN :
Author : James W. Gress
Publisher :
Page : 82 pages
File Size : 27,60 MB
Release : 1968
Category :
ISBN :
Author : P. H. Oosthuizen
Publisher :
Page : 41 pages
File Size : 14,92 MB
Release : 1967
Category : Aerodynamics, Supersonic
ISBN :
A theoretical study of the effects of the wall boundary layer on the supersonic flow around a sharp convex corner is presented. Fundamentally different methods of analysis are adopted for laminar and for turbulent boundary layers. In the case of interactions involving laminar boundary layers, an analysis based on the use of classical boundary layer theory is used. Results of numerical calculations carried out using this analysis to predict the effects of the major governing parameters are presented. In all cases, a considerable upstream and downstream influence is predicted. A simplified form of this analysis, closely related to that of Curle, is also presented, this analysis leading to a simple set of explicit equations describing the flow quantities in the interaction region. Comparison of the simplified analysis with results obtained from the full analysis indicated, as is to be expected, that the simplified analysis will only give acceptable results for small expansion angles and moderate Mach numbers. In the case of turbulent boundary layer interactions, an analysis based on the assumption that there is no upstream influence and that the major portion of the expansion occurs in an effectively inviscid manner is adopted, the flow properties being calculated by the method of rotational characteristics. (Author).
Author : Thomas Johani
Publisher :
Page : 142 pages
File Size : 25,44 MB
Release : 1968
Category :
ISBN :
Author : Franklin K. Moore
Publisher :
Page : 710 pages
File Size : 48,47 MB
Release : 1951
Category : Angle of attack (Aerodynamics)
ISBN :
The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Author : Merritt Albert Thomas
Publisher :
Page : 108 pages
File Size : 43,2 MB
Release : 1968
Category : Boundary layer
ISBN :
Author : Brian Lindsay Hunt
Publisher :
Page : 51 pages
File Size : 11,17 MB
Release : 1964
Category : Aerodinamik, Süpersonik
ISBN :
An analysis of the effect of a sharp convex corner on the momentum thickness of a compressible, supersonic boundary layer flow is presented. The problem is attacked by a momentum integral technique in which an approximate pressure field is used. The shape factor is approximated by a simple expression which is also of general application. The main result of the analysis is an analytic expression for the ratio of the momentum thicknesses downstream and upstream of the corner. The results are also presented graphically over appropriate ranges of the major flow parameters. (Author).
Author :
Publisher :
Page : 1282 pages
File Size : 20,75 MB
Release : 1982
Category : Aeronautics
ISBN :
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author : University of Toronto. Institute of Aerospace Studies
Publisher :
Page : 444 pages
File Size : 32,22 MB
Release : 1968
Category : Aeronautics
ISBN :
Author : Albert L. Braslow
Publisher :
Page : 48 pages
File Size : 43,55 MB
Release : 1959
Category : Numerical analysis
ISBN :
Author :
Publisher :
Page : 60 pages
File Size : 36,70 MB
Release : 1966
Category :
ISBN :