Three-dimensional effects in modeling of dual-mode scramjets

Rodríguez, Cristian; White, J. A.; Riggins, David W.

doi:10.2514/6.2000-3704

Cited by 26 publications

(15 citation statements)

References 18 publications

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“…Rodriguez et al (4) analysed 3D effects in dual mode scramjets. A Wilcox k-ω turbulence model along with a seven species, seven equation finite rate chemistry model was used.…”

Section: Formulation and Solution Methodologymentioning

confidence: 99%

3D numerical simulation of the supersonic combustion of H₂

2006

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A cross-sectional area k turbulent kinetic energy m fuel,in mass flow rate of fuel Ma Mach number P static pressure P 0 local stagnation pressure P 0,inlet inlet stagnation pressure T static temperature T 0 local stagnation temperature T 0,inlet inlet stagnation temperature u velocity along the x-direction Y i mass fraction of species iGreek symbols α local fuel mass fraction α s stoichiometric fuel mass fraction ε turbulent strain rate η c combustion efficiency ABSTRACTResults from numerical simulations of supersonic combustion of H 2 are presented. The combustor has a single stage fuel injection parallel to the main flow from the base of a wedge. The simulations have been performed using FLUENT. Realisable k-ε model has been used for modelling turbulence and single step finite rate chemistry has been used for modelling the H 2 -Air kinetics. All the numerical solutions have been obtained on grids with average value for wall y+ less than 40. Numerically predicted profiles of static pressure, axial velocity, turbulent kinetic energy and static temperature for both non-reacting as well as reacting flows are compared with the experimental data. The RANS calculations are able to predict the mean and fluctuating quantities reasonably well in most regions of the flow field. However, the single step kinetics predicts heat release much more rapid than what was seen in the experiments. Nonetheless, the overall pressure rise in the combustor due to combustion is predicted well. Also, the k-ε model is not able to predict the fluctuating quantities in the base region of the wedge where there is strong anisotropy in the presence of combustion.

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“…Rodriguez et al (4) analysed 3D effects in dual mode scramjets. A Wilcox k-ω turbulence model along with a seven species, seven equation finite rate chemistry model was used.…”

Section: Formulation and Solution Methodologymentioning

confidence: 99%

3D numerical simulation of the supersonic combustion of H₂

2006

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“…Это обусловливает значительный разброс экспериментальных оценок полноты сгорания. В [8] получено значение ψ ≈ 0,8 при числе Маха на входе в камеру горения M b = 2,5. Согласно расчетной оценке, выполненной в [9], при M b = 2,0 ÷ 3,0, α b = 1 (α bкоэффициент избытка воздуха) полнота сгорания составляет ψ = 0,80 ± 0,05.…”

Section: Doi: 1015372/pmtf20150506unclassified

“…Здесь ϑугол впрыска (значение ϑ = 0 соответствует впрыску вдоль потока). Из (6)- (8) определяются скоростьV j1 и температураT j1 , а из уравнения неразрывностидавление:…”

Section: Doi: 1015372/pmtf20150506unclassified

Functional Mathematical Model of a Hydrogen-Driven Combustion Chamber for a Scramjet

2015

PMTF

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“…Distributions of the static pressure and the heat flux over the duct length, which are obtained in experiment, are insufficient for flow identification. The estimate 0.8 ψ ≈ was presented in the work [31] for the Mach number at the combustion chamber inlet M 2.5 e = that corresponds to the flight Mach number M 7.5. It is, however, difficult to determine the distribution of the released heat over the duct length and to subdivide the influence of heat supply and energy dissipation on flow parameters also in this case at an additional measurement of acting forces.…”

Section: Mathematical Model Of Power Plantmentioning

confidence: 99%

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

Latypov

2008

Thermophys. Aeromech.

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Fuel economy at boost trajectory of the aerospace plane was estimated during energy supply to the free stream. Initial and final flight velocities were specified. The model of a gliding flight above cold air in an infinite isobaric thermal wake was used. The fuel consumption rates were compared at optimal trajectory. The calculations were carried out using a combined power plant consisting of ramjet and liquid-propellant engine. An exergy model was built in the first part of the paper to estimate the ramjet thrust and specific impulse. A quadratic dependence on aerodynamic lift was used to estimate the aerodynamic drag of aircraft. The energy for flow heating was obtained at the expense of an equivalent reduction of the exergy of combustion products. The dependencies were obtained for increasing the range coefficient of cruise flight for different Mach numbers. The second part of the paper presents a mathematical model for the boost interval of the aircraft flight trajectory and the computational results for the reduction of fuel consumption at the boost trajectory for a given value of the energy supplied in front of the aircraft.

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Three-dimensional effects in modeling of dual-mode scramjets

Cited by 26 publications

References 18 publications

3D numerical simulation of the supersonic combustion of H₂

3D numerical simulation of the supersonic combustion of H₂

Functional Mathematical Model of a Hydrogen-Driven Combustion Chamber for a Scramjet

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

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Three-dimensional effects in modeling of dual-mode scramjets

Cited by 26 publications

References 18 publications

3D numerical simulation of the supersonic combustion of H2

3D numerical simulation of the supersonic combustion of H2

Functional Mathematical Model of a Hydrogen-Driven Combustion Chamber for a Scramjet

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

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3D numerical simulation of the supersonic combustion of H₂

3D numerical simulation of the supersonic combustion of H₂