Shock Tunnels at ISL

Gnemmi, Patrick; Srulijes, J.; Seiler, F.; Sauerwein, Berthold; Bastide, Myriam; Rey, Christian; Wey, Pierre; Martinez, Bastien; Albers, Hermann; Schlöffel, Gunther; Hruschka, R.; Gauthier, Thibaut

doi:10.1007/978-3-319-23745-9_6

Cited by 5 publications

(3 citation statements)

References 17 publications

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“…The present paper considers experiments conducted at ISL's shock tube laboratory. The shock tunnel B (STB) is capable of providing up to 8 MJ kg −1 to conduct high enthalpy flow experiments [30]. The facility is composed of a shock tube with a Laval nozzle connected to the end of the driven tube, followed by a measurement chamber and a dump tank.…”

Section: B Shock Tunnelmentioning

confidence: 99%

The Measurement of Radar–Plasma Signatures in a Hypersonic Shock Tunnel: Simulation and Experiment

Petervari,

Weidner,

Nekris

et al. 2023

IEEE Trans. Aerosp. Electron. Syst.

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The plasma sheath that forms around a body in hypersonic flight can change the radar signature substantially. The prediction of radar-plasma-signatures, however, is complex, since it incorporates aerothermodynamics and electromagnetics and requires a number of critical assumptions on chemical and aerodynamic parameters as well as on the electromagnetic plasma model. Hence, such an approach requires thorough experimental validation to estimate and reduce its uncertainty. But radar data of hypersonic targets in free flight is extremely rare and, if existing, mostly unavailable. A different validation approach, which This work was funded in the scope of the basic funding of the French and the German MoD and in parts by a dedicated BAAINBw project.

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Section: B Shock Tunnelmentioning

confidence: 99%

The Measurement of Radar–Plasma Signatures in a Hypersonic Shock Tunnel: Simulation and Experiment

Petervari,

Weidner,

Nekris

et al. 2023

IEEE Trans. Aerosp. Electron. Syst.

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“…The facility is described in more details in [10]. For this study, the hypersonic flow is generated by expanding the test gas in a Mach 4.5 contoured nozzle.…”

Section: Experimental Procedures a Hypersonic Facilitymentioning

confidence: 99%

Experimental Investigation of Thermal Ablation by Melting in a Hypersonic Shock Tunnel

Denis¹,

Hruschka²,

Bastide³

et al. 2022

Journal of Spacecraft and Rockets

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In this paper a novel approach for the experimental measurement of the ablation by melting is presented. The experiments are carried out with a hypersonic shock tunnel. The tested models are made of gallium, which melts at low temperatures, allowing the generation and then the measurement of the ablation profiles within only two milliseconds. By means of an optical visualization, the model surface changes are recorded during the experiment. An image post-processing algorithm computes the ablation profiles. The results for two hemisphere-cone models and one hemisphere-cylinder model in a Mach 4.5 nitrogen flow are presented. It is found that the maximum ablation occurs at an angular position of around 30 degrees off-axis rather than at the stagnation point. This is most likely a consequence of the laminar-turbulent transition on the model forebody. Nomenclature Cp= Heat capacity at constant pressurenumber [−] P = Pressure [Pa] or Power flux [W • m −2 ] Re = Reynolds number [−] Re/x = Reynolds number per meter [m −1 ]

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“…The light driver gas is compressed up to 450 bar, and the diaphragm is designed to rupture depending on the conditions of the test [17].…”

Section: Brief Review Of Currently Operating Shock Tubesmentioning

confidence: 99%

Finite element modelling of metallic diaphragm rupture in hypersonic shock tube

Smith¹

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Shock Tunnels at ISL

Cited by 5 publications

References 17 publications

The Measurement of Radar–Plasma Signatures in a Hypersonic Shock Tunnel: Simulation and Experiment

The Measurement of Radar–Plasma Signatures in a Hypersonic Shock Tunnel: Simulation and Experiment

Experimental Investigation of Thermal Ablation by Melting in a Hypersonic Shock Tunnel

Finite element modelling of metallic diaphragm rupture in hypersonic shock tube

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