1 edition of Special course on shock-wave/boundary-layer interactions in supersonic and hypersonic flows. found in the catalog.
Special course on shock-wave/boundary-layer interactions in supersonic and hypersonic flows.
Sponsored by the AGARD Fluid Dynamics Panel and the Von Karman Institute for Fluid Dynamics.
|Series||Agard reports -- 792|
|Contributions||Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel., Von Karman Institute for FluidDynamics.|
interactions - hypersonic viscous interaction similarity parameter – introduction to shock wave boundary layer interactions. UNIT V HIGH TEMPERATURE EFFECTS in HYPERSONIC FLOWS 9 Nature of high temperature flows – chemical effects in air – real and perfect gases – Gibb‟s free. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Development of the Nano Hummingbird: A Tailless Flapping Wing Micro Air Vehicle (English) Can Fundamental Shock-Wave/Boundary-Layer Interaction Research be Relevant to Inlet Aerodynamics? Titchener, Development and Application of Nanoparticle Tracers for PIV in Supersonic and Hypersonic Flows. Chen, F. / Liu, H. / Rong. Aerodynamics of Supersonic Aircraft Name: Institution: Some Physical Aspects of Shock Wave/Boundary Layer Interactions Such disturbances occur in steady transonic or supersonic flows, during explosions, earthquakes, hydraulic jumps and lightning strokes. The ability of shock waves to instantaneously increase the pressure and temperature.
Full text of "Interferometric data for a shock-wave/boundary-layer interaction" See other formats. Shock wave–boundary layer interactions, prediction of turbulence amplification by shocks (currently overpredicted by Reynolds-averaged Navier-Stokes (RANS) methods), 3-D spillage, starting mechanism, and off-design performance. Isolator. Prediction of shock train generated by combustion backpressure or engine contraction ratio, and unsteady.
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Get this from a library. Special course on Shock-wave/boundary-layer interactions in supersonic and hypersonic flows = Interactions entre ondes de choc et couches limites dans les ecoulements supersoniques et hypersoniques.
[North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel.; Von Karman Institute for Fluid Dynamics.;] -. 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 hypersonic vehicles and engines. AGARD/FDP-VKI Special course on Shock Wave/Boundary Layer Interactions in Supersonic and Hypersonic Flows, AGARD Report N o Google Scholar 9.
Regensheit, B. () Drag reduction by suction of the boundary layer separated behind shock wave formation in high Mach numbers (English translation), NACA TM N o Google ScholarCited by: 2.
Knight, D. (), Numerical Simulation of 3-D Shock Wave Turbulent Boundary Layer Interactions, in AGARD/VKI Special Course on Shock-Wave Boundary-Layer Interactions in Supersonic and Hypersonic Flows, Von Karman Institute for Fluid Dynamics, AGARD R, pp.
to Google ScholarCited by: 5. Knight, D., "Numerical Simulation of 3-D Shock Wave Turbulent Boundary Layer Interactions", AGARD/VKI Special Course on Shock-Wave Boundary-Layer Interactions in Supersonic and Hypersonic Flows, AGARD R, Maypp.
to An experimental study is conducted on the interaction of a swept-shock wave with a turbulent boundary layer. The shock wave is generated by a sharp un-swept fin in a Mach 2 flow, where the. Compressible Turbulence in Interactions of Supersonic Flows. It should be noted that in most applications of supersonic to hypersonic flows, shock-wave/boundary-layer interactions have.
Degrez G. Special Course on Shock-Wave/Boundary-Layer Interactions in Supersonic and Hypersonicm Flows. AGARD REPORT, NATO AGARD R Debiève J F, Dupont P. Dependence between the shock and the separation bubble in a shock wave boundary layer interaction. Shock Waves, Délery J, Dussauge J P.
A “Definition” of Hypersonic Flow. A generally accepted value for the lower limit of the hypersonic envelope is Mach 5 (Anderson ). The physical effects that differentiate hypersonic from supersonic flow include thin shock layers, entropy layers, high temperatures, and viscous interactions.
In this paper, the problem of shock wave-boundary layer and shock-shock interactions is not discussed. Indeed, it is a very important topic and the reader is referred to excellent reviews which can be found in various papers.(51's2'92) The experimental simulation of hypersonic flows is also an important topic which is not discussed in this Cited by: 4.
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 : Cambridge University Press.
Written by a leading expert in the field, this book presents a novel method for controlling high-speed flows past aerodynamic shapes using energy deposition via direct current (DC), laser or microwave discharge, and describes selected applications in supersonic and hypersonic flows.
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New. This book fulfils this need and is an introductory textbook intended as a first course in the complex field of aero/fluid mechanics for engineering students. supersonic flows fluid wings chap ratio mach number sec equations reynolds incompressible Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.
CHAPTER 12 HYPERSONIC FLOWS The Five Distinguishing Characteristics Thin Shock Layers Entropy Layers Viscous-Inviscid Interactions High Temperature Effects Low-Density Flows Newtonian Flow Model Stagnation Region Flow-Field Properties Modified.
The effect of micro-vortex generators on shock wave/boundary layer interactions was reviewed. Studies in supersonic flow primarily focused on forward-facing ramps (called micro-ramps) and pairs of tapered vanes (vane pairs). According to published performance comparisons, vane pairs are marginally more effective than by: Aerodynamic Analysis for Complete Configurations in a Supersonic Free Stream Summary Problems References CHAPTER 12 HYPERSONIC FLOWS The Five Distinguishing Characteristics Thin Shock Layers Entropy Layers Viscous-Inviscid Interactions High Temperature Format: On-line Supplement.
The reasons for the difficulty in simulating accurately strong 3-D shock wave/turbulent boundary layer interactions (SBLIs) and high-alpha flows with classical turbulence models are investigated. These flows are characterized by the appearance of strong crossflow separation. In view of recent additional evidence, a previously published flow analysis, which attributes the poor performance of Cited by: 7.
Boggy’s interests were in high-speed aerodynamics, at supersonic and hypersonic speeds, where shock He was later to write a most inﬂuential book Hypersonic Flows Theory with Ronald Probstein*52, as well as another on Gasdynamic Discontinuities.
Two File Size: 2MB. In physics, a shock wave (also spelled shockwave), or shock, is a type of propagating disturbance that moves faster than the local speed of sound in the medium. Like an ordinary wave, a shock wave carries energy and can propagate through a medium but is characterized by an abrupt, nearly discontinuous, change in pressure, temperature, and density of the medium.
From to Kubota was a research associate. He became a faculty member in and was promoted to full Professor in Kubota worked on fluid mechanics, with an emphasis on hypersonic flows, including wakes and shock layers. He also worked on supersonic turbulent shear flows and supersonic boundary layer separation.Course Info; Research.
Centre & Consortiums C.Y. and Wang, J.Y., “Numerical Investigation of Hypersonic Shock-Wave/Boundary-Layer Interactions over a Double-Wedge Configuration,” International Journal of Heat and Y.S.
Chen, and S.M., Liang, “Numerical Analysis on Hypersonic Flows around Blunt-nosed Models and a Space Vehicle.Michael S. Holden, Vice President of the Aeronautics Sector at CUBRC in Buffalo, NY, was internationally recognized principally for his extensive research in supersonic and hypersonic flows.
Dr. Dr. Holden served in many capacities for AIAA and published over papers through AIAA conference proceedings and journal articles.