Heat-transfer Measurements in the Shock-induced Flow Separation Region in a Supersonic Nozzle PDF Download
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Author: L. H. Back
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 925
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Author: L. H. Back
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 925
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Author: A. Naysmith
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 456
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Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Jet propulsion
Languages : en
Pages : 28
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Author: Ulrich Grigull
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 586
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Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Space flight
Languages : en
Pages : 390
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Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
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. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: E. Leon Morrisette
Publisher:
ISBN:
Category : Stratified flow
Languages : en
Pages : 44
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Author: Josef Rom
Publisher:
ISBN:
Category :
Languages : en
Pages : 55
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Heat transfer rates are measured in the separated and reattaching flow regions behind an axisymmetrical backward facing step on a cone-cylinder model, in the high enthalpy laminar supersonic flow in the shock tube. The variation of the local heat transfer rate, divided by the equivalent attached heat transfer rate, behind the separation point is presented at various flow conditions. Shown, also, are the variations of the maximum and average heat transfer rates as functions of Reynolds and shock Mach numbers. Local heat transfer rates are found to vary with distance behind the step and to depend on the combination of Reynolds and shock Mach numbers. The heat transfer rate increases rapidly in the reattachment region and then decreases a little in the attached flow. Both the separation minimum heat transfer rate and the reattachment peak value increase when the Reynolds number is increased and Mach number decreased simultaneously. Peak values from 0.6 to 4 times the equivalent attached values are measured. (Author).
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 92
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