The Aerodynamics Laboratory is equipped with subsonic wind tunnels to explore basic aerodynamics and fluid mechanics. With advanced instrumentation and flow diagnostics, the lab enables researchers to gain unique insights into experimental models and flow regimes. Key areas of research include transient aerodynamics, airfoil icing effects, flow control, motorsports aerodynamics, and wind turbine blade performance. The lab also houses an extensive repository of low Reynolds number airfoil data and propeller performance curves.
The Propulsion Laboratory specializes in research on propulsion and ignition systems. The lab features a low-speed cascade tunnel, jet mixing studies, and continuous combustion units for analyzing heat balance, exhaust gas composition, fuel effects, and flame stability. Modern data acquisition systems provide precise measurements of power, torque, pressure, and temperature, facilitating advanced research and sponsored projects.
The CFD Laboratory serves as a hub for the analysis and optimization of engineering components. The lab focuses on transport phenomena, thermal stress analysis, and engineering applications such as energy conversion, HVAC systems, and aircraft aerodynamics. Equipped with commercial software like ANSYS, MATLAB, CREO, SolidWorks, and SpaceClaim, the lab supports high-performance computing to meet industry and research demands.
The UAV Laboratory is dedicated to the development of low-cost, open-source UAV platforms. It provides infrastructure for flight research in navigation, guidance, and flight control systems to improve UAV safety. The lab also extends its applications to precision farming, environmental surveying, and mapping invasive species, offering significant contributions to integrating UAVs into the national airspace.
The departments Flight Laboratory features a MiG-27 fighter jet, providing students with practical exposure to aircraft subsystems. The Mikoyan MiG-27, a variable-sweep ground-attack aircraft, allows students to gain hands-on experience and insights into the real-world functions of an aircraft.
Additionally, the department has undertaken notable projects, such as the ARDB and SERB-DST-sponsored project titled “Experimental Investigations on Mixing and Combustion in a Modified Dual Combustion Ramjet Engine,” aimed at enhancing combustion efficiency.
Wind Tunnel Specifications
Type of Tunnel: Low speed, Open Circuit, Suction type wind tunnel
Test Section : 0.3 x 0.3×0.6m
Test Velocity Range : 4-30m/s
Contraction Ratio: 16:1
Drive: Axial Flow fan Driven by DC motor with Thyristor speed controller, digital speed indicator and Control unit, 10KW, 1500RPM.
Admissions Open 2025-26