Numerical Simulation and Design of a Radiatively Driven Hypersonic Wind Tunnel PDF Download
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Author: Robert W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages : 360
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Book Description
Author: Robert W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages : 360
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Book Description
Author: George Jarvis Williams
Publisher:
ISBN:
Category :
Languages : en
Pages : 157
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Book Description
Author: R. Miles
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 134
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Book Description
Results and analysis of the RDHWT/MARlAH II 1 MW experiment are reported. The experiment is the addition of approximately MW of energy to a supersonic air flow with an electron bean. The experiment hardware, arrangement and conduct are described. Selected data and analysis are reported. The experiment was subject to transient power fluctuations flat were traced to the electron beam source rather than to flow instability. Power stability was established at lower power conditions. and these data were used for selected code validations.
Author: Frank K. Lu
Publisher: AIAA
ISBN: 9781600864483
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 694
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Book Description
Author: Rudolf Hermann
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 90
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Book Description
In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Author: R. W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Zonglin Jiang
Publisher: Cambridge University Press
ISBN: 1009035673
Category : Technology & Engineering
Languages : en
Pages : 316
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Book Description
Introducing the state-of-the-art of hypervelocity shock tunnels, this complete reference features a variety of drivers and step-by-step introductions to their theories, physics, methods and testing. This book enables researchers and engineers in aerospace to design and improve wind tunnels that simulate flow qualities of real hypersonic flyers.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Work conduced from August 1, 1992 until November 30,1996 under support from the Air Force Arnold Engineering Development Center (AEDC), followed by continuing support from the Air Force Research Laboratory through September 30,1998, established the foundation for the development of a new concept which is expected to extend the range of practical hypersonic wind tunnel testing from approximately Mach 8 to Mach 12 and beyond.
Author: Noor Ahmed
Publisher: BoD – Books on Demand
ISBN: 9535110470
Category : Science
Languages : en
Pages : 232
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Book Description
This book is intended to be a valuable addition to students, engineers, scientists, industrialists, consultants and others providing greater insight into wind tunnel designs and their enormous research potential. It is a compilation of works from world experts on subsonic and supersonic wind tunnel designs, applicable to a diverse range of disciplines. The book is organised in two sections. The first section comprises of three chapters on various aspects of stationary and portable subsonic wind tunnel designs, followed by one chapter on supersonic wind tunnel and the final chapter discusses a method to address unsteadiness effects of fan blade rotation. The second section contains four chapters regarding wind tunnel applications across a multitude of engineering fields including civil, mechanical, chemical and environmental engineering.
