Overview of activities at the ISL hypersonic shock tunnels

Gnemmi, Patrick; Srulijes, J.; Seiler, F.

doi:10.1504/ijesms.2011.038752

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Current Threshold Regulated At 100 a (Test 07-08-12-08-01)1

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Cited by 3 publications

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“…At t = 11.25 ms the plasma is almost extinguished. The displacement of the tip of the projectile model during the plasma discharge is extracted from each interferogram by using an adaption of the Particle-Image Velocimetry software (PIV) used at ISL (Gnemmi et al, 2011). A sub-pixel method with an accuracy of 0.1 pixel allows the detection of the intercorrelation peaks on the images.…”

Section: Current Threshold Regulated At 100 a (Test 07-08-12-08-01)mentioning

confidence: 99%

Guidance of a Supersonic Projectile by a Plasma-Actuation Concept

Gnemmi¹,

Rey²

2011

Wind Tunnels and Experimental Fluid Dynamics Research

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Section: Current Threshold Regulated At 100 a (Test 07-08-12-08-01)mentioning

confidence: 99%

Guidance of a Supersonic Projectile by a Plasma-Actuation Concept

Gnemmi¹,

Rey²

2011

Wind Tunnels and Experimental Fluid Dynamics Research

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ISL Shock Tunnel Operation with Contoured Mach-4.5-6-8-10-Nozzles for Hypersonic Test Applications

Sauerwein

Hruschka

Gnemmi

et al. 2015

29th International Symposium on Shock Waves 1

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Hypersonic flow study in a pneumatically operated academic shock tunnel

Sudarshan¹,

Pranav²,

Sanjay³

2023

Review of Scientific Instruments

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A hypersonic shock tunnel is a primary tool used for basic experimental research and may be used in engineering and university courses to study compressible flows involving shock waves. In the present study, a pneumatically operated shock tunnel is demonstrated for hypersonic flow studies. The high-pressure nitrogen gas is used to drive a pneumatic cylinder, which is used to burst the thin metal diaphragms. Tunnel-free stream conditions are quantified using the measured pressure values and by applying shock tube relations. The free-stream Mach number of 5.5–7.2 is achieved by varying the bursting pressure and test gas pressure from 2.1 to 4.5 bars and 0.2 to 0.5 bar, respectively. The simulation is performed and the shock standoff distance quantified, and the stagnation pressures measured. The results demonstrate that the pneumatically operated tunnel enhanced operation capacity compared to the manually operated tunnel and well suits the academic hypersonic research and developmental activities.

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Overview of activities at the ISL hypersonic shock tunnels

Cited by 3 publications

References 8 publications

Guidance of a Supersonic Projectile by a Plasma-Actuation Concept

Guidance of a Supersonic Projectile by a Plasma-Actuation Concept

ISL Shock Tunnel Operation with Contoured Mach-4.5-6-8-10-Nozzles for Hypersonic Test Applications

Hypersonic flow study in a pneumatically operated academic shock tunnel

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