Numerical study of free-piston shock tunnel performance

Tani, Kazuo; Itoh, Katsuhiro; Takahashi, Masahiro; Tanno, Hideyuki; Komuro, Tomoyuki; Matsubara, Hiroshi

doi:10.1007/bf01415829

Cited by 24 publications

(10 citation statements)

References 8 publications

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“…For example, the reflected shock tunnel simulations of [Jacobs (1994)] and [Tani et al (1994)] typically produce pressure histories that are within 10% of the experimental measurements over the period of useful test flow produced by the facility. However, substantial differences between the simulated and experimental shock compression processes can usually be observed within either the pressure history or shock speed comparisons.…”

Section: Introductionmentioning

confidence: 95%

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Simulation of Oxford University Gun Tunnel performance using a quasi-one-dimensional model

2002

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The performance of the Oxford University Gun Tunnel has been estimated using a quasi-onedimensional simulation of the facility gas dynamics. The modelling of the actual facility area variations so as to adequately simulate both shock reflection and flow discharge processes has been considered in some detail. Test gas stagnation pressure and temperature histories are compared with experimental measurements at two different operating conditions -one with nitrogen and the other with carbon dioxide as the test gas. It is demonstrated that both the simulated pressures and temperatures are typically within 3% of the experimental measurements.

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Section: Introductionmentioning

confidence: 95%

“…A number of different quasi-one-dimensional numerical formulations for the solution of impulse facility operation have been described by [Groth et al (1991)], [Jacobs (1994)], and [Tani et al (1994)]. …”

Section: Introductionmentioning

confidence: 99%

Simulation of Oxford University Gun Tunnel performance using a quasi-one-dimensional model

2002

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“…As discussed in the design of HIEST, because pressure and heat losses occur, numerical analysis cannot reproduce experiments without considering these effects. [15][16][17] However, this analysis assumes isentropic process to predict the maximum attainable pressure and find the optimum operational conditions. As shown in Fig.…”

Section: Compression By Free Piston and Attainable Pres-mentioning

confidence: 99%

Development of Shock Tube for Ground Testing Reentry Aerothermodynamics

Yamada

Suzuki

Takayanagi

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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A free-piston double-diaphragm shock tube with 70 Â 70 mm cross-section at test section is newly developed to investigate thermochemical nonequilibrium phenomena behind a shock wave. This paper presents the performance of the shock tube and the measurement system newly developed. Experimental investigations to clarify its characteristics are conducted for various operational parameters, such as rupture pressure of the first diaphragm and initial pressures in the low-pressure tube, the high-pressure tube, and the compression tube. Based on the characteristics experiment, a performance map of the shock tube is obtained by changing the operation parameters. The result shows that the shock tube can generate the post-shock condition corresponding to super-orbital reentry flight conditions. The newly developed measurement system enables us to obtain a spatial distribution of spectra behind a shock wave with high spatial and time resolution. A description of the measurement system and typical examples of the measured spectra are presented.

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“…Rather, the test time, in principle, is determined from the nonlinear wave interactions occurring in the test gas slug. 15 The unsteady, one-dimensional compressible ow solver originally developed for designing the High-Enthalpy Shock Tunnel (HI-EST), Kakuda Research Center, National Aerospace Laboratory, Kakuda, Japan, 16 is used with appropriate modi cations for numerically simulating the free-piston-driver operation. In the numerical simulation, to specify the criterion for the soft landing, the residual velocity of the piston colliding against the CT end wall is assumed to be lower than 10 m/s.…”

Section: Driver Operation Designmentioning

confidence: 99%

Effective Test Time Evaluation in High-Enthalpy Expansion Tube

et al. 2001

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Flow characterization experiments of stagnation enthalpies up to 37 MJ/kg are carried out in the recently commissioned expansion tube facility. The features and the effective duration time of the test ow eld are determined not only from static and pitot pressures but also by observing the temporal variation of radiating emission from a shock layer around a spherical forebody. The thickness of the radiating layer matches well with the numerical results. The arrival time of the contact surface between the acceleration and test gases is better identi ed both as a decrease in the radiating layer thickness and from the emission spectroscopy. The useful test time is determined by integrating the mentioned measurements.

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Numerical study of free-piston shock tunnel performance

Cited by 24 publications

References 8 publications

Simulation of Oxford University Gun Tunnel performance using a quasi-one-dimensional model

Simulation of Oxford University Gun Tunnel performance using a quasi-one-dimensional model

Development of Shock Tube for Ground Testing Reentry Aerothermodynamics

Effective Test Time Evaluation in High-Enthalpy Expansion Tube

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