Development of the Shock Tunnel and Its Application to Hypersonic Flight

Hertzberg, A.; Wittliff, Charles E.; Hall, J. G.

doi:10.1016/b978-0-12-395595-1.50034-9

Cited by 8 publications

(3 citation statements)

References 29 publications

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“…The shock tube has limitations in terms of flow Mach number capabilities (Lukasiewicz, 1973). Hertzberg et al (1962) originally suggested a modification to the conventional shock tube in order to generate hypersonic Mach numbers. A convergent-diverging nozzle added to the end of the low pressure section (driven section) of a conventional shock tube permits the establishment of steady flow Mach numbers, far exceeding those that can be achieved using a conventional shock tube.…”

Section: Principles Of Operationmentioning

confidence: 99%

An Experimental Evaluation of Transient Flows in Supersonic Gun Tunnel

Amir

Yusoff²,

Ahmed

2012

Int J Automot Mech Eng

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An experimental study has been performed to investigate transient flows in a supersonic gun tunnel. The experimental work was performed using a short duration high speed flow test facility at the Universiti Tenaga Nasional (UNITEN). A physical description of the facility along with the principles of operation is provided. The pressure history of the flow process was captured using a fast response pressure transducer at three stations located at the end of the facility. Experimental measurements of shock strength, peak pressure and shock wave speed change of Air-Air as a driver/driven gas are then presented and compared with a further set of experimental measurements using the gas combination of Helium-Air. The shock wave speed was measured experimentally with a two pressure transducers technique. The results showed that the existence of the piston has a very significant influence on both the moving shock wave and peak pressure value achieved. The results provide a very good estimate for the above-mentioned parameters obtained after diaphragm rupture, and also provide a better understanding of the parameters that affect the performance of the facility.

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Section: Principles Of Operationmentioning

confidence: 99%

An Experimental Evaluation of Transient Flows in Supersonic Gun Tunnel

Amir

Yusoff²,

Ahmed

2012

Int J Automot Mech Eng

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“…In conventional shock tunnels using heated hydrogen as driver gas or helium heated by internal combustion, it has been possible to achieve tailored interface operation up to shock Mach numbers slightly in excess of 10 in air. 2 This yields a test section stagnation enthalpy that corresponds to flight velocities of about 16,000 fps. To produce higher test section enthalpies, higher shock speeds are required.…”

Section: Introductionmentioning

confidence: 99%

A study of the free-piston shock tunnel.

Stalker

1967

AIAA Journal

208

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“…Studies in high velocity, hypersonic gas dynamics, have, for many years, been carried out with the aid of the reflect ed shock tunnel (e.g. Hertzberg et al (1961) Holder and Schultz (1961)). The shock tube, from which the reflected shock tunnel is derived, is capable of producing hypersonic flows with higher stagnation enthalpies and higher densities than can be realised in the reflected shock tunnel.…”

mentioning

confidence: 99%

The production of pulsed nozzle flows in a shock tube

Mudford

Stalker

1976

9th Fluid and PlasmaDynamics Conference

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Firstly, I would like to thank my supervisor, Dr. R. J. Stalker, for the invaluable help and guidance which he has given me during the time that we have worked together. I am also indebted to him for the design of the hardware for the modification to the shock tunnel and for the original concept for the modification. I would also like to thank Dr. Hans Hornung and Dr. John Sandeman for their generous assistance, given on innumerable occasions. There are many other people to whom I am indebted: to Mr. Roland French, Mr. Vic Adams and Mr. Gavin Spackman for their help in performing the experiments, maintaining the equipment and running the tunnel and shock tube safely and efficiently; to Mr. Ken Smith for his photographic work and the helpful advice he has given in this field; to Mr. Len Batt and Mr. David King for repair and mainten ance of the electronic equipment; to the workshop staff of the Physics Department for the production of several pieces of apparatus all of which have been of high quality. My thanks go also to my fellow post-graduate students, notably Doug Kewley, Nizar Ebrahim, Graham Caldersmith, John Baird and Mike Daffey, for the many stimulating and helpful discussions we have had. I extend my thanks to Ms. Julie Faux, not only for typing this thesis, but for going, with me, through all the traumas of its compilation. Finally, I wish to express my appreciation to the Australian Government for their provision of a Commonwealth Scholarship and to the Australian Research Grants Committee for the funding of the research.

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Development of the Shock Tunnel and Its Application to Hypersonic Flight

Cited by 8 publications

References 29 publications

An Experimental Evaluation of Transient Flows in Supersonic Gun Tunnel

An Experimental Evaluation of Transient Flows in Supersonic Gun Tunnel

A study of the free-piston shock tunnel.

The production of pulsed nozzle flows in a shock tube

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