Aerospace Testing Equipment
State-of-the-art laboratory infrastructure designed for undergraduate and postgraduate aeronautical research, facilitating hands-on experimentation in aerodynamics and propulsion.
Propeller Test Rig
This propeller test rig is designed to measure the aerodynamic performance and efficiency of different propeller designs. Students conduct tests to determine thrust and torque coefficients as functions of the advance ratio in a controlled environment. Key measurements include motor power input, rotational speed, and static thrust output. Learning outcomes focus on momentum theory and the optimization of propeller blade pitch for specific flight regimes. It is a key tool for students exploring low-speed propulsion and unmanned aerial vehicle (UAV) design.
Supersonic Wind Tunnel (Blowdown)
The blowdown supersonic wind tunnel is designed for high-Mach number studies, including shock wave visualization using Schlieren or shadowgraph systems. Students investigate compressible flow characteristics around wedges, cones, and diamond-shaped airfoils at speeds exceeding Mach 1.5. Key measurements include stagnation pressure, static pressure distributions, and Mach angle calculations from flow imagery. It provides critical insights into wave drag and expansion fan interactions. This rig is essential for advanced courses in high-speed aerodynamics and gas dynamics.
Smoke Tunnel
Designed for qualitative flow visualization, the smoke tunnel allows students to observe streamline behavior over various geometric bodies. By injecting paraffin-based smoke, engineers can identify flow separation points, wake regions, and vortex shedding in real-time. It is particularly effective for demonstrating the effects of angle of attack on stalling and the role of flow control devices like slats or flaps. Learning outcomes focus on the intuitive understanding of fluid motion and aerodynamic interference. This unit is an invaluable tool for conceptual teaching and visual learning.
Cascade Tunnel
The cascade tunnel is specialized for evaluating the performance of turbine or compressor blade profiles in a linear arrangement. Students measure total pressure loss and flow deflection across the blade row to understand stage efficiency in turbomachinery. Key measurements include wake traverses and surface pressure distribution on the central blade of the cascade. Learning outcomes involve blade loading analysis and the study of secondary flow losses. It bridges the gap between basic aerodynamics and the design of modern axial flow engines.
Jet Propulsion Test Rig
This test rig features a small-scale centrifugal or axial flow gas turbine engine equipped for performance mapping. Students conduct experiments to calculate thrust, specific fuel consumption, and thermal efficiency across varying RPM ranges. Key measurements involve inlet and exhaust temperatures, compressor pressure ratios, and fuel flow rates. Learning outcomes include understanding the Brayton cycle and engine component characteristics under load. It provides engineering students with a realistic platform for studying aerospace propulsion systems and energy conversion.
Rocket Motor Test Stand
The rocket motor test stand is engineered for measuring the static thrust and pressure-time history of solid or liquid propellant rocket motors. Students analyze impulse parameters and burn rates to evaluate motor performance and propellant batch consistency. Key measurements include load cell thrust data, chamber pressure, and propellant mass flow rates. Learning outcomes focus on internal ballistics and nozzle expansion efficiency. This rig ensures students gain practical exposure to the high-energy dynamics of aerospace launch systems.
Aircraft Structures Rig
This structural test rig is used to study the stress and strain distribution in aircraft components like thin-walled beams and wing sections. Students perform bending, torsion, and combined loading tests utilizing strain gauge bridges and data acquisition systems. Key measurements include deflection profiles and shear center identification for various cross-sections. Learning outcomes focus on the principles of aeroelasticity and structural integrity under operational loads. It is vital for teaching aerospace structural analysis and aircraft design optimization.
Landing Gear Model
The landing gear model demonstrates the kinematics and shock absorption mechanisms of typical aircraft undercarriage systems. Students explore the damping characteristics of oleo-pneumatic struts and the mechanical sequencing of extension and retraction cycles. Key measurements include impact loads, drop test deflection, and hydraulic pressure requirements. Learning outcomes involve understanding energy dissipation during landing and structural load paths to the fuselage. This model provides a detailed look into critical aircraft subsystems and maintenance engineering.
Airfoil Pressure Distribution Setup
This setup features a specialized airfoil model with surface pressure taps connected to a multi-channel digital manometer. Students map the pressure coefficient along the chord at various angles of attack in a wind tunnel flow. Key measurements allow for the calculation of the lift coefficient via pressure integration, allowing comparison with theoretical data. Learning outcomes focus on the Kutta-Joukowski theorem and the onset of airfoil stall. It is a fundamental experiment for validating aerodynamic theory through empirical laboratory testing.
Flight Simulator Trainer
The flight simulator trainer provides an interactive environment for students to study flight dynamics, stability, and control loop responses. It allows for the simulation of various aircraft configurations and environmental conditions to observe pilot-in-the-loop interactions. Key measurements include control surface deflections and resulting aircraft state variables (pitch, roll, yaw rates). Learning outcomes involve understanding longitudinal and lateral stability modes. This trainer is essential for teaching control systems and human factors in aeronautical engineering.