Hypersonic detonation wave powered lifting-propulsive bodies

Atamanchuk, T.; Sislian, J. P.

doi:10.2514/6.1991-5010

Cited by 7 publications

(2 citation statements)

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“…The use of a stabilized d eto n atio n w ave (either norm al or oblique) for supersonic aircraft propulsion (see, for exam ple, D unlap et al (1958), Sargent & Gross (1960), M orrison (1978, O strander et al (1987) andA tam anchuk &Sislian (1991), ram accelerator (H ertzberg et al 1988) or a detonation-driven hollow projectile (T hibault et al 1992;Zhang et al 1993) relies on th e establishm ent of the detonation wave behind th e th ro a t of th e nozzle to provide positive th ru st. The stab ility of the d etonation w ave is essential because it determ ines w hether a standing-w ave configuration can be obtained w ithin an engine from the tran sien t startin g conditions.…”

Section: Introductionmentioning

confidence: 99%

Effects of area change and friction on detonation stability in supersonic ducts

Zhang

Chue

Frost

et al. 1995

Proc. R. Soc. Lond. A

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The stability of a detonation wave passing through opposed supersonic flow in a duct of varying cross section and with friction is studied numerically by a transient quasi-one-dimensional model, taking into account the unsteady motion of the duct and using a single-step Arrhenius reaction scheme. The analysis indicates that in a converging duct, that is, a nozzle raising the rate of area change drives a detonation wave towards instability, and adding roughness behind the shock front increases the detonation velocity and stabilizes the detonation wave. The stable detonation-wave configuration can be analysed by replacing the classical Chapman-Jouguet criterion with a generalized sonic choking condition based on the competition between area change, friction and heat release.

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Section: Introductionmentioning

confidence: 99%

Effects of area change and friction on detonation stability in supersonic ducts

Zhang

Chue

Frost

et al. 1995

Proc. R. Soc. Lond. A

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“…1960, Ostrander et al 1987 andSislian 1990) and vehicle design studies (Atamanchuk and Sislian 1991) indicate that this concept may have some merit. However, it is speculative and the main focus of present-day high-speed propulsion research (~u r t h~ and Curran 1991) is on the more traditional supersonic combustion ramjet or scramjet combustor approach.…”

Section: Introductionmentioning

confidence: 99%

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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Two-Gamma Jump Relations for Gaseous Detonation Waves

Liu

1998

GCST

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Accurate jump relations for Chapman-Jouguet (CJ) and overdriven gaseous detonation waves are derived. The difficulty in accurately approximating the energy equation in a perfect gas twogamma detonation jump formulation is resolved by adjusting the authentic combustion heat release in terms of linearly approximated up-and down-stream sensible enthalpies at the CJ condition where it is exactly satisfied for CJ and well approximated for overdriven waves. The basis of the success of the derived two-gamma jump relations is explained. Explicit thermodynamic jump relations across a normal detonation wave are obtained. These approximate jump relations depend on the following four parameters: /10 upstream isentropic exponent (or the gamma giving pertinent upstream sound speed for defining M ,); '"(J. CJ isentropic exponent (or the gamma giving pertinent sound speed for a CJ state); M h upstream Mach number; and MJ, CJ Mach number. '"(J and M J can be obtained numerically, or experimentally with the derived jump relations. Comparisons of exact numerical and the present approximate calculation for jump conditions of CJ and overdriven detonations for methane-and hydrogenoxygen systems show excellent agreement over a wide range of upstream Mach number, temperature, pressure, and mixture conditions.

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Hypersonic detonation wave powered lifting-propulsive bodies

Cited by 7 publications

References 0 publications

Effects of area change and friction on detonation stability in supersonic ducts

Effects of area change and friction on detonation stability in supersonic ducts

Detonation Waves and Propulsion

Two-Gamma Jump Relations for Gaseous Detonation Waves

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