Simulation of unsteady hypersonic combustion around projectiles in an expansion tube

Yungster, Shaye; Radhakrishnan, Krishnan

doi:10.2514/6.1999-2640

Cited by 2 publications

(2 citation statements)

References 18 publications

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“…A more detailed study of shock-wave and boundary-layer interaction on the projectile and tube wall surfaces is presented by Yungster (1992). Time-accurate calculations for chemically reactive flow in expansion tubes were performed by the same authors, Choi et al (1999) and Yungster and Radhakrishnan (2001). Again, Choi et al (2000a, b) examine oscillating shock-induced combustion, as experimentally recorded by Lehr (1972).…”

Section: Introductionmentioning

confidence: 99%

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

Ess

Allen

2005

International Journal of Numerical Methods for Heat &Amp; Fluid Flow

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Purpose -A computational fluid dynamics code for the calculation of laminar hypersonic multi-species gas flows in chemical non-equilibrium in axisymmetric or two-dimensional configuration on shared and distributed memory parallel computers is presented and validated. The code is designed to work efficiently in combination with an automatic domain decompositioning method developed to facilitate efficient parallel computations of various flow problems. Design/methodology/approach -The baseline implicit numerical method developed is the lower-upper symmetric Gauss-Seidel scheme, which is combined with a sub-iteration scheme to achieve time-accuracy up to third-order. The spatial discretisation is based on Roe's flux-difference splitting and various non-linear flux limiters maintaining total-variation diminishing properties and up to third-order spatial accuracy in continuous regions of flow. The domain subdivision procedure is designed to work for single-and multi-block domains without being constrained by the block boundaries, and an arbitrary number of processors used for the computation. Findings -The code developed reproduces accurately various types of flows, e.g. flow over a flat plate, diffusive mixing and oscillating shock induced combustion around a projectile fired into premixed gas, and demonstrates close to linear scalability within limits of load imbalance.Research limitations/implications -The cases considered are axisymmetric or two-dimensional, and assume laminar flow. An extension to three-dimensional turbulent flows is left for future work. Originality/value -Results of a parallel computation, utilising a newly developed automatic domain subdivision procedure, for oscillating shock-induced combustion around a projectile and various other cases are presented. The influence of entropy correction in Roe's flux-difference splitting algorithm on diffusive mixing of multi-species flows was examined.

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Section: Introductionmentioning

confidence: 99%

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

Ess

Allen

2005

International Journal of Numerical Methods for Heat &Amp; Fluid Flow

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“…Oldenborg, R.C (1989) worked on critical reaction rates in hypersonic combustion chemistry and found that High Mach number flight also results in very short residence times (millisecond time range) in a hypersonic engine which causes poor chemical combustion efficiency. S. Yungster and K. Radhakrishnan (2001) worked on simulation of unsteady hypersonic combustion around projectiles in an expansion tube and found that the flame propagation produces a series of oblique shock waves that reignite the core flow, creating an oblique detonation wave whose interaction with the laterally expanding boundary layer flame gives rise to a normal detonation wave that propagates. K. Kumaran and V. Babu (2009) worked on investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of Hydrogen.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Hydrogen-Fueled Scramjet Combustor with Parallel Strut Fuel Injector at a Flight Mach Number of 6

Pandey

Roga

Choubey

2016

JAFM

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A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 6 with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack (α=-4°, α=0°, α=4°) have been studied for parallel injection. The scramjet configuration used here is a modified version of DLR scramjet model. Fuel is injected at supersonic speed (M=2) through a parallel strut injector. For parallel injection, the shape of the strut is chosen in a way to produce strong stream wise vorticity and thus to enhance the hydrogen/air mixing inside the combustor. These numerical simulations are aimed to study the flow structure, supersonic mixing, and combustion phenomena for the three different types of geometries along with circular shaped strut configuration.

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Simulation of unsteady hypersonic combustion around projectiles in an expansion tube

Cited by 2 publications

References 18 publications

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

Numerical Investigation on Hydrogen-Fueled Scramjet Combustor with Parallel Strut Fuel Injector at a Flight Mach Number of 6

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