The Turbulent Shear Flow Physics and Engineering Laboratory at IISc in engaged in experimental research over a wide range of Mach numbers, starting from a low subsonic value and going up to Mach 10. Four different wind tunnels allow us to span this Mach number range. The largest of the four facilities is the Roddam Narasimha Hypersonic Wind Tunnel (RNHWT), a 0.5 m diameter enclosed free-jet facility, which can be operated between Mach numbers 6 and 10. The RNHWT facility will be showcased during the tour.
Combustion Research and Advanced Diagnostics Laboratory (CRADL) deals with supersonic combustion experiments. This facility can handle mass flow rate of fuel from 0.6 to 1.5 kg/s. Static temperature and pressure varies from 800 K to 1050 K and 0.5 bar to 1 bar respectively. Total temperature and pressure are in the range of 1600 K to 1800 K and 5.3 bar to 10 bar. In these conditions, a run time of 13 seconds can be achieved. To operate at higher Mach numbers, liquid fuel heater can be incorporated which uses Methane or hydrogen as fuel.
Laboratory for Hypersonic and Shockwave Research (LHSR) is a place of interdisciplinary research varying from hypersonic aerodynamics to various applications of shock waves. Shock tubes form an important asset of the lab for carrying out experiments and shock tunnels that can operate in the range of Mach 6 to Mach 14 with specific enthalpy reaching as high as 5 MJ/kg help in achieving desired flow conditions. The tunnel test sections can accommodate models as large as 100 mm in diameter and 1 m in length. The Free Piston Driven Shock Tube(FPST) that uses free piston to compress gas in the driver tube is a state of the art facility that helps achieve higher enthalpies. Impact of shock waves on chemical kinetics of fuels, materials response, medical applications, industrial technology development etc., have been some of the interdisciplinary areas of the research of this lab. In this visit various facilities of the lab shall be shown.
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