Free Piston Shock Tunnels HEG, HIEST, T4 and T5

Hannemann, Klaus; Itoh, Katsuhiro; Mee, D. J.; Hornung, H. G.

doi:10.1007/978-3-319-23745-9_7

Cited by 23 publications

(23 citation statements)

References 78 publications

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“…A large deal of research focuses on the scale effects of the test model and the actual aircraft 1,2 , but little research has been published on the scale effects of the high enthalpy nozzle 3 , especially the thermochemical non-equilibrium scale effects on the high enthalpy tunnel simulation ability. There are many high enthalpy tunnels in the world, such as TCM2 4 , HEG 5 ,T4 6 , T5 6 , HIEST 6 , JF-10 7 , LENS I 8 , and FD-21 9 . Due to the complexity and di culty of the hypervelocity simulation, a great number of national and international space and hypersonic ight projects have been carried out extensively, such as integrated scramjet con guration 10 , complex hypersonic ight con guration 10 , and hypersonic boundary layer transition 11 .…”

Section: Introductionmentioning

confidence: 99%

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The thermochemical non-equilibrium scale effects of the high enthalpy nozzle

Shen

et al. 2020

Preprint

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Abstract The high enthalpy nozzle converts the high enthalpy stagnation gas into the hypervelocity free flow. The flow region of the high enthalpy nozzle consists of three parts: an equilibrium region upstream of the throat, a non-equilibrium region near the throat, and a frozen region downstream of the throat. Here we propose to consider the thermochemical non-equilibrium scale effects in the high enthalpy nozzle. With numerical solving axisymmetric compressible Navier-Stokes equations coupling with Park’s two-temperature model, the fully non-equilibrium solution is employed throughout the entire nozzle. Calculations are performed at different stagnation conditions with the different absolute scales and expansion ratio. The results of this study contain twofold. Firstly, as the absolute scale and expansion ratio increase, the freezing position is delayed, and the flow approaches equilibrium. Secondly, the vibrational temperature and Mach number decrease with the increase in the nozzle scale and expansion ratio，while the speed of sound, static pressure, and translational temperature increase as the nozzle scale and expansion ratio increase.

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Section: Introductionmentioning

confidence: 99%

“…piston shock tunnel in the world 14,15 . + , N 2 + , e -) are used to calculate the high enthalpy ow eld 1,6,8,11 .…”

Section: Introductionmentioning

confidence: 99%

The thermochemical non-equilibrium scale effects of the high enthalpy nozzle

Shen

et al. 2020

Preprint

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“…Different types of piston motions can be enforced to generate various flow fields, which may include shock waves, contact discontinuities, and smooth regions. Indeed, this setup is often the core of experimental test-rig arrangements thanks to its feasibility and flexibility [45,46,47,48]. However, the numerical simulation of these flow fields is challenging due to the presence of traveling waves with different spatial scales, and it represents a valuable test to assess the capabilities of the proposed adaptive method.…”

Section: Introductionmentioning

confidence: 99%

An adaptive ALE scheme for non-ideal compressible fluid dynamics over dynamic unstructured meshes

Guardone

2018

Shock Waves

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This paper investigates the application of mesh adaptation techniques in the Non-Ideal Compressible Fluid Dynamic (NICFD) regime, a region near the vapor-liquid saturation curve where the flow behavior significantly departs from the ideal gas model, as indicated by a value of the fundamental derivative of gasdynamics less than one. A recent interpolation-free finite-volume adaptive scheme is exploited to modify the grid connectivity in a conservative way, and the governing equations for compressible inviscid flows are solved within the Arbitrary Lagrangian Eulerian framework by including special fictitious fluxes representing volume modifications due to mesh adaptation. The absence of interpolation of the solution to the new grid prevents spurious oscillations that may make the solution of the flow field in the NICFD regime more difficult and less robust. Non-ideal gas effects are taken into account by adopting the polytropic Peng-Robinson thermodynamic model. The numerical results focus on the problem of a piston moving in a tube filled with siloxane MD 4 M, a simple configuration which can be the core of experimental research activities aiming at investigating the thermodynamic behavior of NICFD flows. Several numerical tests involving different piston movements and initial states in 2D and 3D assess the capability of the proposed adaption technique to correctly capture compression and expansion waves, as well as the generation and propagation of shock waves, in the NICFD and in the non-classical regime.

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“…The operation of the reflected shock tunnel is discussed by Hannemann [19] and shown in Figure 1.2. In summary, it is an adaptation of the basic shock tube where a converging diverging nozzle is placed at the end of the tube.…”

Section: Problem Backgroundmentioning

confidence: 99%

“…Hannemann et al [19] have summarised a number of free piston shock tunnels which are currently in use. Among them are HEG, HIEST, T4, and T5.…”

Section: Brief Review Of Currently Operating Shock Tubesmentioning

confidence: 99%