Aerodynamics and Fluid Mechanics
The Aerodynamics and Fluid mechanics research group at IIT Kharagpur explores a diverse range of topics with a variety of approaches. Numerical work includes development of high accuracy numerical schemes for incompressible and compressible flow using higher order and compact schemes. Experimental work involves use of wind tunnels, water tank, etc accompanied by measurement instruments like PIV, flow visualization techniques, high precision load cells and balances & pressure scanners to investigate various flow problems like fixed and flapping wings, train models, bluff bodies, sub boundary layer vortex generators in supersonic flow etc. The broad areas of research are summarized as follows: DNS and LES of compressible nozzle and diffuser flows, active and passive control of jets in various configurations, jet aeroacoustics, bluff body flow control, fixed and flapping wing aerodynamics, high enthalpy flows, Lagrangian coherent structures, aerodynamic study of high speed train configurations, multiphase flow simulations in hybrid rocket combustors, shock wave boundary layer interactions, RCS jet in supersonic cross flow and chaff cloud aerodynamics.
Current research activities include: Direct Numerical Simulation (DNS) and Large-eddy Simulation (LES) of compressible turbulent flow in nozzles & diffusers, LES of shock-turbulence interaction in supersonic pipe & diffuser flows, prediction of flow transition for hypersonic flows, experimental studies on controlled shock-boundary layer interactions in hypersonic intake, slosh dynamics and fluid structure interaction, experimental investigation of low aspect ratio rigid wing executing main flapping, pitch and heave motions, bio-inspired drag reduction of low Reynolds number flyers, investigation on the distribution of absorbed energy after a laser induced breakdown in quiescent air, and aerodynamic design of traction rolling stock with speed potentials of 250 km/h upgradeable up to 350 km/h.
The suction-type low speed subsonic tunnel has a test section size of 61cm X 61cm. The wind speed in the test section may be varied from 18m/sec to 35m/sec. Experiments related to measurement of surface pressure distribution as well as overall forces and moments on a variety of models are conducted in the tunnel, using 3-component electronic wind tunnel balance.
Airflow Bench is a compact low speed wind tunnel where air speed in the test section can be varied continuously upto 33m/sec. Using different test sections, severel experiments involving flow visualisation, measurement of pressure, forces and moments as well as boundry layer in favourable and adverse pressure gradiants are conducted on small models.
In this blow down tunnel, supersonic flow at Mach number 2.2 is achieved in the 5cm X 10cm test section. The tunnel is equipped with a Schliren system for shock observation.
The gust tunnel has a test section size of 61cm X 91.5cm where wind speed can be varied continuously upto 34m/sec. Models under steady and oscillatory flow conditions can be used to measure various performance parameters.
The Industrial tunnel has a test section of size 2.25m X 1.5m. This is built for applications involving studies of atmospheric boundary layer, road vehicle aerodynamics, air pollution etc. The maximum speed in the test section is 16m/sec.