Performance variation of scramjet nozzle at various nozzle pressure ratios

Hiraiwa, Tetsuo; Tomioka, Sadatake; Ueda, Shuuichi; Mitani, Tohru; Yamamoto, Masahiko; Matsumoto, Masashi

doi:10.2514/3.23858

Cited by 11 publications

(4 citation statements)

References 4 publications

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“…A representative nozzle is designed for the typical hydrogen fueled hypersonic flight vehicle with a flight condition corresponding to Mach 8 at an altitude of 30 km. The nozzle inlet parameters are typical values [3] , inlet Mach of 2.5, static pressure of 0.05 MPa, and static temperature of 2100K. A fully integrated scramjet is one that employs the entire windward surface of the afterbody in the exhaust expansion process.…”

Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Zhang

Qin

Liu

2014

AMM

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The chemical non-equilibrium flow of supersonic combustion ramjet (scramjet) nozzle is numerical simulated with different chemical kinetic models to research the effects on numerical results of the nozzle performance. The numerical results show that total temperature is increased due to the recombination of dissociation compositions and the combustion of the residual fuel. The effect of the combustion of the residual fuel is more obvious in this paper, and the effect to the performance of the nozzle is noticeable. The species of the compositions in the models influence the quantity of heat sending out when it get equilibrium, so the 9-species chemical kinetic models are more suitable in the simulation of the scramjet nozzle chemical non-equilibrium flows.

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Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Zhang

Qin

Liu

2014

AMM

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“…In this paper, the SERN is chose from the ref [5]. The inlet size of nozzle is 32mm×147.3mm, the total length of nozzle is 520mm and the length of the lower plate is 150mm.…”

Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

“…(1)(2)(3)(4)(5) are Elementary reactions dissociation-recombination; equations(6)(7)(8)(9)(10)(11)(12) are Elementary exchange reactions…”

mentioning

confidence: 99%

Numerical Simulation of Chemical Non-Equilibrium Flow in Hydrocarbon Fuel Scramjet Nozzle

Zhang

Liu

et al. 2013

AMR

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Based on 8-specice, 12-step finite-rate chemical reaction models, the chemical non-equilibrium flows of hydrocarbon fuel scramjet single expansion ramp nozzle (SERN) were numerical simulated. The chemical dynamic characteristics of flow in SERN were analyzed in detail. The performances of SERN were compared at various inlet static temperatures. The numerical results show that the chemical non-equilibrium effect had great influence on the performance of the nozzle at the relatively high inlet static temperature. However, influence induced by chemical non-equilibrium effect can be neglected when nozzle inlet static temperature is less than 2500K.

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“…Finally, it is remarked that over expansion of the nozzle flow should be avoided as it can result in losses of thrust and lift. Hiraiwa et al (1995) investigated the effects of ambient pressure on the flow inside a planar SERN. The expansion angle at the start of the nozzle was chosen as 15°.…”

Section: General Analyses Of Nozzle and Vehicle Performancementioning

confidence: 99%

Design of a 3D shape transitioning nozzle and experimental thrust measurements of an airframe integrated scramjet

Kunze¹

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Performance variation of scramjet nozzle at various nozzle pressure ratios

Cited by 11 publications

References 4 publications

Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Numerical Simulation of Chemical Non-Equilibrium Flow in Hydrocarbon Fuel Scramjet Nozzle

Design of a 3D shape transitioning nozzle and experimental thrust measurements of an airframe integrated scramjet

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