2 edition of On the interaction of a laminar hypersonic boundary layer and a corner expansion wave found in the catalog.
On the interaction of a laminar hypersonic boundary layer and a corner expansion wave
Philip A. Sullivan
by Institute for Aerospace Studies, University of Toronto] in [Toronto
Written in English
Includes bibliographical references.
|Statement||by Philip A. Sullivan.|
|Series||UTIAS technical note ;, no. 129|
|LC Classifications||TL507 .T6 no. 129|
|The Physical Object|
|Pagination||vi, 15 p.|
|Number of Pages||15|
|LC Control Number||70473289|
Written by best-selling author, John D. Anderson, Jr., this book covers the subject of sustained hypersonic flight, the technology behind the Space Shuttle and other high speed flight vehicles. Anderson's book offers timely and up-to-date information on hypersonic flow-an area that has grown explosively in the last decade. This proceedings book presents the results of the 31st International Symposium on Shock Waves (ISSW31), held in Nagoya, Japan in It covers among others blast waves, chemical reacting flows, chemical kinetics, detonation and combustion, flow visualization, and shock waves in .
There are complex corner vortex flows in a rectangular hypersonic inlet/isolator. The corner vortex propagates downstream and interacts with the shocks and expansion waves in the isolator repeatedly. The supersonic corner vortex in a generic hypersonic inlet/isolator model is theoretically and numerically analyzed at a freestream Mach number of The cross-flow Cited by: Full text of "Interferometric data for a shock-wave/boundary-layer interaction" See other formats.
Structure of multiple shock-wave/turbulent boundary-layer interactions in a rectangular duct Asymptotic defect boundary layer applied to nonequilibrium laminar hypersonic air flows Analysis of nonequilibrium, hypersonic blunt-body flow with the local-similarity method. A complex flow structure often includes a lip shock wave associated with the beveled expansion fan and wake trail adjacent to the shear layer confluence. The corner expansion process is an expansion fan pattern changed by the presence of the approaching boundary layer and radius of the bevel or shoulder, RC. The wake flow features show several Author: Rakhab C. Mehta.
State by State School Guide, 1994-95
Dental manpower needs in New England.
Aquifer tests at the Jackpile-Paguate uranium mine, Pueblo of Laguna, west-central New Mexico
Soldiers and the Gold Coast
speak of freedom
Principles of engineering economic analysis
David Hartley, M.P.
Theme and variations
resource bank on self-esteem
Most Precious Blood Parish, Hyde Park, Massachusetts
Bridging the gap: Student to professional actor
An investigation of an oblique shock wave/laminar boundary layer interaction is presented. The Mach number was 2. 15, the Reynolds number was 10**5 and the overall pressure ratio was 1. Rapid expansion of a supersonic boundary layer and its application to the near wake. Interaction of a laminar hypersonic boundary layer and a corner expansion wave.
PHILIP A. SULLIVAN ; Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion by: Abstract. Shock wave/boundary layer interaction in laminar, two-dimensional compression corner flow is investigated at high enthalpy.
High enthalpy flows exhibit a smaller scale of interaction which is in accordance with calculations based on momentum integral theory and experimental observations behind a rearward facing by: 8. Hypersonic shock-wave laminar boundary-layer interaction Delery  has shown that the upstream influence, a measure of the intensity of shock-wave boundary-layer interaction, increases with the ramp angle for fixed Mach and Reynolds numbers, and decreases with the Mach number for fixed ramp angle and Reynolds number; the separation length Cited by: Request PDF | On Jun 5,Doyle D.
Knight and others published Hypersonic Shock Wave Transitional Boundary Layer Interactions - A Review | Find, read. The hypersonic laminar boundary layer near sharp compression and expansion corners 29 March | Journal of Fluid Mechanics, Vol. 63, No.
3 Shock Wave Boundary-Layer Interactions in Laminar Transonic FlowCited by: 1. Chapman, D. Kuehn, and H. Larson, “ Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition,” NACA Technical ReportGoogle Scholar; 2.
Holden, “ A study of flow separation in regions of shock wave-boundary layer interaction in hypersonic flow,” AIAA Paper No.Cited by: Melnik, R.E.
and Grossman, B. () Further developments in an analysis of the interaction of a weak normal shock wave with a turbulent boundary layer. Symposium Transsonicum II, (eds.: K. Oswatitsch and D. Rues), Springer-Verlag, –Cited by: The first type is normally labelled a viscous interaction, and will be described in this section.
The second type of interaction is called a shock wave-boundary layer interaction and will be described in the next section. A viscous interaction is a pressure interaction between the hypersonic boundary layer and outer inviscid flow.
The goal of this study is to assess CFD capability for the prediction of shock wave laminar boundary layer interactions at hypersonic velocities. More specifically, the flow field over a double-cone configuration is simulated using both perfect gas and non-equilibrium Navier–Stokes models.
Computations are compared with recent experimental data obtained from Cited by: 2. The capability for CFD prediction of hypersonic shock wave laminar boundary layer interaction was assessed for a double wedge model at Mach in air and nitrogen at MJ/kg and 8 MJ/kg comprising four cases.
The experimental data is surface heat transfer measurements and schlieren by: Investigation on Turbulent Expansion-Corner Flow With Shock Impingement Shock Wave and Boundary Layer Interaction in the Presence of an Expansion Corner – Hawbolt, R.
J., Sullivan, P. A., and Gottlieb, J. J.,“Experimental Study of Shock Wave and Hypersonic Boundary Layer Interactions Near a Convex Corner,” AIAA Cited by: 4. A supersonic expansion fan, technically known as Prandtl–Meyer expansion fan, a two-dimensional simple wave, is a centered expansion process that occurs when a supersonic flow turns around a convex corner.
The fan consists of an infinite number of Mach waves, diverging from a sharp a flow turns around a smooth and circular corner, these waves can. Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gasdynamics and frequently a defining feature in high speed aerodynamic flowfields.
The interactions can be found in practical situations, ranging from transonic aircraft wings to. A method for analyzing the interaction of an oblique shock wave with a boundary layer / (Washington, D.C.: National Aeronautics and Space Administration, ), by William C. Rose, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust).
Roshko, A. & Thomke, G. Supersonic, turbulent boundary-layer interaction with a compression corner at very high Reynolds number. In Viscous Interaction Phenomena in Supersonic and Hypersonic Flow, pp. – University of Dayton Press, by: A comprehensive survey is given of the state of knowledge of steady, nonturbulent laminar fluid wakes behind both blunt and slender bodies in viscous fluids, with emphasis on high-speed wakes.
The flows are generally assumed to occur at large but finite free-stream Reynolds numbers, generally with a thin boundary layer on the body. Compressible and viscous flow. () Incipient Separation in Laminar Ramp-Induced Shock-Wave/Boundary-Layer Interactions.
AIAA Journal() Direct numerical simulation of a compressible boundary-layer flow past an isolated three-dimensional hump in a high-speed subsonic by: This volume contains papers of presentations delivered during the "Seventh IUTAM Symposium on Laminar-Turbulent Transition" in Stockholm, Sweden, June The areas of emphasis include: Novel approaches to receptivity analysis and transition modelling.
Non-normal effects and global modes. Abstract Laminar-turbulent transition in a hypersonic boundary layer can be inﬂuenced by imperfections on the wall surface.
Transition can be delayed or accelerated depending on the type, conﬁguration and location of the imperfections.
Both natural transition and the transition triggered by the imperfections are poorly understood. This. Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.Shock wave boundary layer interaction can result in peak heat loads an order of magnitude or more above stagnation point heating values.
A classic example is ﬂight number 2– of the X in which a test model pylon mounted beneath the fuselage disintegrated due to the impingement of a supersonic jet generated by a shock-shock File Size: 2MB.
() Analysis of the interaction of a weak normal shock wave with a turbulent boundary layer. 7th Fluid and PlasmaDynamics Conference. () On Kuo's Solution for Laminar Viscous Flow past a Finite Flat by: