Heat Transfer in the Region of Interaction of an Oblique Shock Wave and a Laminar Boundary Layer PDF Download
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Author: William John Cook
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 252
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Author: William John Cook
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 252
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Book Description
Author: William C. Rose
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 28
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Book Description
Method for predicting interaction produced by externally generated, oblique shock wave impinging on laminar or turbulent boundary layers.
Author: C. E. Gulbran
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 168
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Book Description
Author: John V. Becker
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 36
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Book Description
Author: B. K. Hodge
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
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Book Description
This report presents the results of an investigation of hypersonic laminar boundary-layer/shock-wave interactions using the method of MacCormack to solve the time-dependent compressible Navier-Stokes equations. Comparisons of the numerical solutions with experimental data were made to ascertain the validity of the numerical method and to identify regions of anomalous behavior. The algorithm gave good results when applied to hypersonic laminar interactions that caused either small or no separated regions and marginal performance when applied to hypersonic laminar interactions having large regions of separated flow. The extents of the separated regions in interactions having large regions of separated flow were underpredicted when compared with experimental data. The predicted wall heat-transfer rates exhibited the correct qualitative trend but not the experimentally measured quantitative values. Consideration of the effects of needed stabilizing terms as well as grid resolution suggests inadequate mesh spacing in the longitudinal direction as the cause of the aforementioned anomalies. If inadequate mesh spacing (and the corresponding lack of support for every term of the Navier-Stokes equations) is a prime cause of the cited discrepancies between the numerical results and the experimental data, then the needed reduction of several orders of magnitude in delta x, would increase CPU time and core storage requirements to untenable levels. (Author).
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: Mohammad Ali Badr
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 44
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Book Description
Shock wave laminar boundary layer interaction (SWBLI) over a double wedge was simulated at Mach 7.11 with stagnation enthalpy of 2 MJ/kg (low enthalpy case), and at Mach 7.14 with stagnation enthalpy of 8 MJ/kg (high enthalpy case) using the commercial flow solver GASPex. An inviscid simulation was performed at Mach 7.14 for validation and solution justification. In the inviscid case, the region downstream of the first shock wave shows less than one percent difference for any flow parameter in comparison with oblique shock wave theory. In both cases, the flow is assumed to be laminar. The computed heat transfer distribution agrees closely with the experiment at the time reported by experiment where the flow reaches steady state; however, significant difference are evident in the duration in which the flow reaches steady state in the computation. In particular, the time-accurate simulations indicate a significantly longer physical time to achieve steady state than observed in the experiment.
Author: Louis G. Kaufman
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
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Book Description
Author: A. Martellucci
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 138
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Book Description
Author: Paul F. Holloway
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 106
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Book Description
