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Relevant bibliographies by topics / Free Piston Driven Hypersonic Shock Tunnel HST3 (FPST)

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Academic literature on the topic 'Free Piston Driven Hypersonic Shock Tunnel HST3 (FPST)'

Author: Grafiati

Published: 6 September 2023

Last updated: 31 July 2025

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Journal articles on the topic "Free Piston Driven Hypersonic Shock Tunnel HST3 (FPST)"

1

Kumar, C. S., and K. P. J. Reddy. "Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds." Journal of Heat Transfer 135, no. 12 (2013). http://dx.doi.org/10.1115/1.4024667.

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Heat transfer rates measured in front and to the side of a protrusion on an aluminum flat plate subjected to hypersonic flow at zero angle of attack are presented for two flow enthalpies of approximately 2 MJ/kg and 4.5 MJ/kg. Experiments were conducted in the hypersonic shock tunnel (HST2) and free piston driven HST3 at a freestream Mach number of 8. Heat transfer data was obtained for different geometries of the protrusion of a height of 4 mm, which is approximately the local boundary layer thickness. Comparatively high rates of heat transfer were obtained at regions of flow circulation in t

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Dissertations / Theses on the topic "Free Piston Driven Hypersonic Shock Tunnel HST3 (FPST)"

1

Srinath, S. "Development of Novel Heat Transfer Gauges Based on Large Carbon Clusters to Measure Total as well as Radiative Heat Flux for Planetary Entry Configurations in Hypersonic Shock Tunnels." Thesis, 2017. http://etd.iisc.ac.in/handle/2005/4243.

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The quest of travelling beyond earth, preludes with ground based experimental studies, detailed analysis and accurate calculations in the aspects of having a safer design of flying vehicles. As the vehicles plunge into the dense atmosphere with greater velocities to hypersonic Mach numbers, the shockwave produced ahead of the aerodynamic body becomes highly intense producing volatile conditions at a temperature of several thousands of Kelvins. Predominantly the unsteady effects are dominated by radiations in the velocities which are greater than 6km/s. During such high enthalpy flows, the atmo

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2

Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ac.in/handle/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu

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3

Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ernet.in/2005/3848.

Full text

Abstract:

One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu

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4

Jayaram, V. "Experimental Investigations Of Surface Interactions Of Shock Heated Gases On High Temperature Materials Using High Enthalpy Shock Tubes." Thesis, 2007. https://etd.iisc.ac.in/handle/2005/495.

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The re-entry space vehicles encounter high temperatures when they enter the earth atmosphere and the high temperature air in the shock layer around the body undergoes partial dissociation. Also, the gas molecules injected into the shock layer from the ablative thermal protection system (TPS) undergo pyrolysis which helps in reducing the net heat flux to the vehicle surface. The chemical species due to the pyrolysis add complexity to the stagnation flow chemistry (52 chemical reactions) models which include species like NOx, CO and hydrocarbons (HCs). Although the ablative TPS is responsible fo

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5

Jayaram, V. "Experimental Investigations Of Surface Interactions Of Shock Heated Gases On High Temperature Materials Using High Enthalpy Shock Tubes." Thesis, 2007. http://hdl.handle.net/2005/495.

Full text

Abstract:

The re-entry space vehicles encounter high temperatures when they enter the earth atmosphere and the high temperature air in the shock layer around the body undergoes partial dissociation. Also, the gas molecules injected into the shock layer from the ablative thermal protection system (TPS) undergo pyrolysis which helps in reducing the net heat flux to the vehicle surface. The chemical species due to the pyrolysis add complexity to the stagnation flow chemistry (52 chemical reactions) models which include species like NOx, CO and hydrocarbons (HCs). Although the ablative TPS is responsible fo

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