Diffraction and transmission of a detonation into a bounding explosive layer

Liu, J.C.; Liou, J.J.; Sichel, Martin; Kauffman, C. W.; Nicholls, J. A.

doi:10.1016/s0082-0784(88)80397-7

Cited by 26 publications

(18 citation statements)

References 4 publications

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“…When hydrogen or helium was used in the inert layer, the reaction zone was observed to propagate at 50% of the CJ velocity. The studies of layered mixtures of Liu 11 and Jones 12 also did not report higher than CJ velocities and pressures, apparently because these studies focused on diffraction phenomena during the initial formation of the detonation in the surrounding layer.…”

Section: Non-uniform Mixturesmentioning

confidence: 99%

Cryogenic, Multiphase, Hydrogen-Oxygen Detonations

Coy¹,

Watts²,

Palaniswamy³

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information , 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) NUMBER(S)Edwards AFB CA 93524-7048 AFRL-PR-ED-JA-2005-027 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited. SUPPLEMENTARY NOTESPresented at ABSTRACTDetonations of flowing mixtures of hydrogen and oxygen at temperatures between 90 and 110 K, pressures from 3 to 5 bar, and mixture densities of 3-6 kg/m3 have been studied. The effect of liquid oxygen on wave speeds and peak wall pressures are reported. Data taken at cryogenic conditions are compared with ambient temperature data taken at similar initial densities and equivalence ratios, as well as with equilibrium, Chapman-Jouget theory calculations. For the conditions studied, liquid oxygen was found to result in increased wave speeds and peak wall pressures. These observations are shown to be consistent with a highly stratified mixture with high concentrations of oxygen in a layer adjacent to the wall and low concentrations along the axis of the tube. Detonations of flowing mixtures of hydrogen and oxygen at temperatures between 90 and 110 K, pressures from 3 to 5 bar, and mixture densities of 3-6 kg/m 3 have been studied. The effect of liquid oxygen on wave speeds and peak wall pressures are reported. Data taken at cryogenic conditions are compared with ambient temperature data taken at similar initial densities and equivalence ratios, as well as with equilibrium, Chapman-Jouget theory calculations. For the conditions studied, liquid oxygen was found to result in increased wave speeds and peak wall pressures. These observations are shown to be consistent with a highly stratified mixture with high concentrations of oxygen in a layer adjacent to the wall and low concentrations along the axis of the tube. I. IntroductionHIS paper presents results from an investigation of detonations of flowing mixtures of cryogenic gaseous hydrogen and liquid oxygen. This work was undertaken to support development of pulse detonation rocket engines (PDRE). Cryogenic propellants will be desirable for PDRE applications for many of the same reasons that they are used for conventional rocket engines: the density is increased, which reduces tank volume, and...

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Section: Non-uniform Mixturesmentioning

confidence: 99%

Cryogenic, Multiphase, Hydrogen-Oxygen Detonations

Coy¹,

Watts²,

Palaniswamy³

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…Oblique detonations have actually been observed in only one type of experiment, the two-layer detonations of Liu et al 1987, Liu et al 1988and Dabora et al 1991. A channel is divided longitudinally by a rigid partition terminating in a flexible film or diaphragm, Fig.…”

Section: Experiments On Bcstationary" Detonation Wavesmentioning

confidence: 99%

“…After the transient initiation processes have ceased, the oblique detonation wave angle can be predicted (Liu et al 1987) by a simple steady flow analysis in the frame of the shock intersection located at the boundary between the primary and secondary layers. In general, a reflected wave (usually an expansion) is produced in the products of the primary explosive in order to match the flow deflection angle and pressure at the contact surface between the products of the primary and secondary explosive.…”

Section: Experiments On Bcstationary" Detonation Wavesmentioning

confidence: 99%

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Detonation Waves and Propulsion

Shepherd

1994

ICASE/LaRC Interdisciplinary Series in Science and Engineering

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The possibility of using a detonation wave as the key combustion system for supersonic propulsion is examined. A brief review of propagating detonations is provided first. This review emphasizes the unique and unstable nature of the coupling between reaction zone and shock waves that characterize detonations. The theory of idealized, steady, oblique detonation waves and their reaction zone structure are summarized. The evidence for the existence of stabilized or steady oblique detonations is discussed. Experiments with multiple layers of explosive and projectiles fired into explosive gases are examined. There are a variety of reasons that these previous studies have failed to produce stabilized detonations. A brief catalog of difficulties is provided and based on andogies with our knowledge of propagating detonations, a set of criteria are proposed for the existence and stability of stabilized detonations. The problems of initiation and instability are examined for the situation of a flow over a wedge.

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“…(Gross and Chinitz, 1960), (Nicholls, 1963), (Rubins and Rhodes, 1963), (Behrens, et al, 1965), (Strehlow, 1968), (Strehlow and Crooker, 1974), (Lehr, 1972), and (Liu, et al, 1986). Of potential relevance, especially in light of Dunlap et al's concern, are dramatic observations of one-and three-dimensional detonation instabilities.…”

Section: Reviewmentioning

confidence: 99%

Oblique Detonations: Theory and Propulsion Applications

Powers

1994

ICASE/LaRC Interdisciplinary Series in Science and Engineering

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The oblique detonation, a combustion process initiated by an oblique shock, arises in most supersonic combustion applications including, most notably, the ram accelerator and the oblique detonation wave engine. Additionally, it is the generic two-dimensional compressible shocked reacting flow; consequently, its basic research value is inherent. The outstanding theoretical questions are also the fundamental practical questions: e.g. what conditions are necessary for steady solutions, what is the dependency of the steady propagation speed on the ambient condition, what is the susceptibility of the system to instability, and what is the behavior of the system in unsteady operation. A related topic which transcends all questions is the ability to describe these phenomena computationally. At this early stage, these issues are most clearly addressed with simple models. This paper will review the application of such models to oblique detonations and discuss their future relevance.

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Diffraction and transmission of a detonation into a bounding explosive layer

Cited by 26 publications

References 4 publications

Cryogenic, Multiphase, Hydrogen-Oxygen Detonations

Cryogenic, Multiphase, Hydrogen-Oxygen Detonations

Detonation Waves and Propulsion

Oblique Detonations: Theory and Propulsion Applications

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