Airbreathing propulsion concepts for high speed tactical missiles

Zarlingo, F.

doi:10.2514/6.1988-3070

Cited by 3 publications

(2 citation statements)

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“…The frequency factor A is 1:42 3 10 11 m 3 =kmol×s, and the activation energy E is 125:52 kJ=mol (30 kcal=mol). The exponents a, b, and m have values of 0.1, 1.65, and 0, respectively (Zarlingo 1988). The unit of _ v CxHy is kg=m 3 s. Fig.…”

Section: Governing Equationsmentioning

confidence: 99%

“…A booster nozzle, however, creates additional reliability problems, such as the dynamic impact of the nozzle ejection on the vehicle and the increase in the time delay from the rocket to the ramjet phase. A nozzleless booster, using the propellant grain as a nozzle, has been used to circumvent the difficulties inherent in an ejectable nozzle (Waltrup et al 2002;Zarlingo 1988). During the booster phase, the combustor functions as a conventional rocket combustor, closed at the forward end, with a suitable nozzle formed by the propellant grain at the aft end, as shown schematically in Fig.…”

Section: Introductionmentioning

confidence: 99%

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Unified Analysis of Internal Flowfield in an Integrated Rocket Ramjet Engine. I: Transition from Rocket Booster to Ramjet Sustainer

Sung

Yang

2014

J. Aerosp. Eng.

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A comprehensive numerical analysis was conducted to study the internal flow development in an integrated rocket-ramjet (IRR) propulsion system. The study consists of two parts: transition from the rocket booster to the ramjet sustainer and combustion dynamics during ramjet operation. The physical model of concern includes the entire IRR flow path, extending from the leading edge of the inlet center body through the exhaust nozzle. The theoretical formulation is based on the Farve-averaged conservation equations of mass, momentum, energy, and species concentration in axisymmetric coordinates and accommodates finite-rate chemical kinetics and variable thermophysical properties. Turbulence closure is achieved using a low-Reynolds-number k-ɛ two-equation model. The governing equations are solved numerically by means of a finite-volume preconditioned flux-differencing scheme capable of treating a chemically reacting flow over a wide range of Mach numbers. Various important physiochemical processes involved in the transition from the booster to the sustainer phase are investigated systemically. Emphasis is placed on the flow interactions between the inlet diffuser and combustor. The effects of operation timing on the flow evolution, fuel spread, ignition, and flame development are studied.

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Section: Governing Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%