Shock Tube Simulation of Low Mach Number Blast Waves

Morgan, Richard G.; Gildfind, David

doi:10.1007/978-3-319-16835-7_11

Cited by 2 publications

(2 citation statements)

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“…One source is the growth of the boundary layer in the test slug and driver gas, which serves to attenuate the shock by entraining mass from the core flow [1,4]. The motion of the contact surface, the interface between the expanded driver gas and test gas, also produces waves which affect the shock speed [5]. The behaviour of the contact surface is itself dependent on many factors including the driver technology employed, the driver condition chosen for the experiment, and the primary diaphragm rupture behaviour [6].…”

Section: Introductionmentioning

confidence: 99%

LASTA 2.0: Validation of a Reverse Time Integration Method

Steer,

Clarke,

McGilvray

et al. 2024

AIAA SCITECH 2024 Forum

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Shock tube experiments provide critical insight into the thermochemical processes that occur in the shock layer of hypersonic flight vehicles and are used to validate many chemical-kinetic and radiative models for vehicle design. Shock tube flows exhibit a number of non-ideal behaviours that must be accounted for when interpreting experimental data. Previous work has shown that variations in shock speed and boundary layer growth along the length of the shock tube have a strong effect on the test slug properties. The LAgrangian Shock Tube Analysis code (LASTA) is an a posteriori tool that successfully addressed this problem, allowing reconstruction of the test slug from an experimentally obtained shock trajectory. LASTA 2.0 is presented here, which further constrains the test slug properties using an additional experimental pressure boundary condition whose effects are included via a backwards time integration scheme. The tool is validated against ideal gas cases following accelerating and decelerating shock trajectories, each with a tube-end Mach number of 6.5 and a fill pressure of 66.66 Pa. Agreement between the method and results from a viscous, axisymmetric Navier-Stokes solution is found to be within 1% in pressure and temperature in the majority of cases. Improved agreement with experimental data is evident when compared to the previous version of LASTA, particularly where there is strong shock speed non-uniformity.

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Section: Introductionmentioning

confidence: 99%

LASTA 2.0: Validation of a Reverse Time Integration Method

Steer,

Clarke,

McGilvray

et al. 2024

AIAA SCITECH 2024 Forum

View full text Add to dashboard Cite

show abstract

“…The driver also causes further waves to reach the shock. This is due to having a finite driver section length, change in volume if a free piston driver is used or transient heating processes if a deflagration, detonation or arc heating driver are used [2]. Additionally, the diaphragm rupture is not an instantaneous process and can introduce a rapid acceleration of the shock and subsequent deceleration, substantially influencing shock tube performance [3,4].…”

Section: Introductionmentioning

confidence: 99%

Analytical Method of Evaluating Nonuniformities in Shock Tube Flows: Theory and Development

McGilvray

Mare

2022

AIAA Journal

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Shock tube experiments are a cornerstone of investigations into the hypersonic flight environment. However, the actual flow through the basic shock tube has not been well characterised in the literature, and nonuniformities arising in the test gases are not well understood. This work produces a quasi-one-dimensional analytical methodology for predicting the nonuniformities in the post-shock test gas based exclusively on the experimentally measured history of shock speed down the tube. Wave effects extracted from shock speed variations are shown to provide all information necessary in order to reconstruct the test slug from any particular experiment. Accurate representation of flow dynamics is initially checked against Argon test cases following accelerating and decelerating shock trajectories, each with a tube-end Mach number of 6.5 and a fill pressure of 66.66 Pa in a tube of 100 mm diameter. Agreement between the method and results from a viscous, axisymmetric Navier-Stokes solution is found to within 1% in pressure and temperature.

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Shock Tube Simulation of Low Mach Number Blast Waves

Cited by 2 publications

References 1 publication

LASTA 2.0: Validation of a Reverse Time Integration Method

LASTA 2.0: Validation of a Reverse Time Integration Method

Analytical Method of Evaluating Nonuniformities in Shock Tube Flows: Theory and Development

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