The Shock Layer Concept and Three-dimensional Hypersonic Boundary Layers
Author : Hsien Kei Cheng
Publisher :
Page : 50 pages
File Size : 18,28 MB
Release : 1961
Category : Aerodynamics, Hypersonic
ISBN :
Author : Hsien Kei Cheng
Publisher :
Page : 50 pages
File Size : 18,28 MB
Release : 1961
Category : Aerodynamics, Hypersonic
ISBN :
Author : Marvin I. Kussoy
Publisher :
Page : 32 pages
File Size : 14,13 MB
Release : 1989
Category : Aerodynamics, Hypersonic
ISBN :
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 28 pages
File Size : 42,10 MB
Release : 2018-07-02
Category :
ISBN : 9781722182298
Experimental data for a series of two- and three-dimensional shock wave/turbulent boundary layer interaction flows at Mach 7 are presented. Test bodies, composed of simple geometric shapes, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface-pressure and heat-transfer distributions as well as limited mean-flow-field surveys in both the undisturbed and the interaction regimes. The data are presented in a convenient form for use in validating existing or future computational models of these generic hypersonic flows. Kussoy, Marvin I. and Horstman, Clifford C. Ames Research Center NCC2-452; RTOP 505-80-11...
Author : Roger L. Kimmel
Publisher :
Page : 83 pages
File Size : 40,48 MB
Release : 1997-12-01
Category :
ISBN : 9781423547921
The stability and transition of three-dimensional boundary layers was studied. In the first phase of the investigation, arrays of hot film probes were used to measure the three-dimensional structure of instability waves on an axisymmetric cone at Mach 8. In the second phase, linear stability theory was used to design a cone with an elliptic cross section, which was also tested at Mach 8. Results show that disturbances on the axisymmetric cone travel in wave packets with predominantly zero wave angle. On the elliptic cone, only weak evidence for stationary waves was found. The predominant waves were traveling waves at about 12 kHz. Additional waves, probably second mode, occurred near 80 kHz.
Author : C. Herbert Law
Publisher :
Page : 52 pages
File Size : 37,94 MB
Release : 1975
Category : Aerodynamic heating
ISBN :
Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
Author : Kristian Petterson
Publisher :
Page : pages
File Size : 11,45 MB
Release : 1998
Category :
ISBN :
Author : M. I. Kussoy
Publisher :
Page : pages
File Size : 46,79 MB
Release : 1991
Category :
ISBN :
Author : R. R. Boyce
Publisher :
Page : pages
File Size : 30,76 MB
Release : 2000
Category :
ISBN :
Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel
Publisher :
Page : 62 pages
File Size : 39,64 MB
Release : 1968
Category : Aerodynamics, Hypersonic
ISBN :
Author : William H. Dorrance
Publisher : Courier Dover Publications
Page : 353 pages
File Size : 34,69 MB
Release : 2017-05-22
Category : Technology & Engineering
ISBN : 0486822583
Designed for advanced undergraduate and graduate courses in modern boundary-layer theory, this frequently cited work offers a self-contained treatment of theories for treating laminar and turbulent boundary layers of reacting gas mixtures. 1962 edition.