Subsonic wind tunnel
The subsonic, suction type non-return wind tunnel has 6:1 contraction ratio. The tunnel aids in understanding the flow field and pressure distribution around various geometric shapes of engineering and academic interest (viz: flat plate, cylinder and aerofoils). Flow field visualizations are carried out using a green laser, whereas the pressure distributions are obtained through a 32-port electronic pressure scanner.
Subsonic Tunnel
Specifications:
- Test section 600x600 mm
- Length of the test section 4 meters
- Maximum test section velocity 45 m/s
- Contraction ratio 6:1
- Maximum power 22KW
- Maximum RPM:1500
- Diameter of the Propeller blade: 1.3m
- Turbulence level: Below 2%
Flow visualization over an aircraft model
Flow past an aerofoil at 10° angle of attack a) Symmetric Aerofoil b) Cambered Aerofoil
Supersonic wind tunnel
Blow down type supersonic wind tunnel, operates in the range of Mach number (M = 1.5 to 3.5). A 14.14 cubic meter storage tank delivers air at 20 bar. Desired Mach number in the test section is obtained by varying the nozzles. Schlieren and Shadowgraph techniques are used to demonstrate/understand the dynamics of shock waves for varying Mach numbers for flow past a wedge and the blunt nose of cylindrical cone.
Supersonic Tunnel
Specifications:
- Test section dimension 100X100 mm
- Range of Mach No:1.5 to 3.5
- Maximum Stagnation pressure: 10 bars
- Test duration: 20 sec. nominal
- Pressure measurement :16 port pressure scanner
- Volume of Pressure tank:14.14 m3
- Maximum Pressure storage capacity: 20 bars
- 20 hp Compressors-with air coolers and dryers
Flow visualization over an aircraft model
Test Section and Flow past double wedged Aerofoil at M=2 a) Schlieren b) Shadowgraph
Open Jet facility
Flow acoustics and exhaust flow characteristics are complemented with a supersonic open jet facility, which can operate at M = 2.5.
Open jet facility
Specifications:
- Blow down type
- Maximum Mach No:2.5
- Maximum Stagnation pressure: 10 bars
- Test duration: 100 sec. nominal
- Pressure measurement :16 port pressure scanner
- Volume of Pressure tank:14.14 m3
- Maximum Pressure storage capacity: 20 bars
- 20 hp Compressors-with air coolers and dryers
- Nozzle exit diameter=25 mm (max.)
Flow visualization over an aircraft model
Twin-jet expansion using color Schlieren technique
Shock tube Facility
The shock tube is an instrument used to replicate and direct blast waves at a sensor or a model in order to simulate actual explosions and their effects, usually on a smaller scale. Shock tubes are also used to investigate compressible flow phenomena and gas phase combustion reactions.
Shock tube test facility
Specifications:
- ID 80 mm, OD 116 mm
- Driver section length: 2 m
- Driven section length: 1.5 m to 11.5 m.
- Contraction ratio 6:1
- Data Acquisition system
- NI-based PXI -1031 chassis
- Signal Conditioner 482 series PCB piezotronics
- GUI with Lab-view
- Sensors/Detectors
- High frequency PCB pressure transducer
- CH* emission measurement with the help of photo diode
- Pressure transducers
High Altitude Test Facility
The high altitude test facility consists of a high pressure compressor, vacuum pump and a vacuum tank. The central part of the HAT is the vacuum tank. It is evacuated by the vacuum pump to provide the required vacuum. Inside this tank the nozzle and free jet region are located. It is equipped with two oppositely located windows in order to offer a path for the light beams of the Schlieren system.
High Altitude Test Facility
Specifications:
- Tank is 1 m dia and 2 m long
- Pressure range: 0.001 bar to 20 bar
- Velocities: Mach 1.5 to 4
Kinetic Heating Simulation Facility
Kinetic Heating Simulation facility is an experimental scheme which simulates the convective heating experienced by an aerodynamic body (in ascend heating) by dynamically heating the test article by radiation panels. The process is achieved through a closed loop heating system.
Kinetic Heating Simulation facility
Applications:
- Design validation of Thermal protection system for aerodynamic heating of rockets, heat shields etc.
- Performance evaluation of thermal paints
- New light weight Material development which can withstand high heat flux
Water Tunnel
Applications:
- Flow visualization of models in underwater applications.
- Tracing of stream line, streak line and path line flow under various Reynolds Numbers.
- Effect of high Reynolds flow over the model.
Water Tunnel
Specifications:
- Test section 0.18*0.25*0.46m (W*H*L)
- Flow velocity 0.05-0.13m/s
- Capacity 300 liters
- Turbulence intensity <0.5% RMS
Injector Calibration facility
Applications:
Injector Calibration facility
Injector Calibration Facility
Specifications:
- Flow rates- 0.01 to 1 kg/sec
- Duration – 10-30 sec
- Max overhead pressure – 30 bar
Measurements:
- Pressure drop vs. Volumetric flow
- Temperature measurement of the propellants
- Uniformity of droplets by high speed photography
- Spray angle
Rocket Engine Test Rig
Rocket engine test stand facility is used to test a static rocket engine for various operating condition. The propellant used are Lox- Kerosene or Lox- H2 gas. The maximum design thrust is 500 kgf for duration of 20 sec.
Rocket Engine Test Rig
Measurements:
- Thrust
- Chamber pressure
- Ignition delay
- Thrust chamber skin temperature
- Propellant flow rates
- Propellant temperature
Jet Engine
The Rolls-Royce Avon was the first axial flow jet engine designed and produced by Rolls-Royce. Introduced in 1950, the engine went on to become one of their most successful post-World War II engine designs. It was used in a wide variety of aircraft, both military and civilian, as well as versions for stationary and maritime power.
Jet Engine
General characteristics:
- Type: Turbojet
- Length: 2602 mm
- Diameter: 760 mm
- Dry weight: 2,890 lb (1,310 kg)
Components:
- Compressor: axial flow
- Combustors: cannular
- Turbine: two-stage axial flow
- Fuel type: kerosene based
Universal Testing Machine (UTM)
UTM is used to determine the tensile strength of a given specimen by generating stress verses strain graphs. Mechanical properties such as modulus of elasticity, yield strength and ultimate strength can be determined for the given material.
Capacity: 20 kN
Universal Testing Machine(UTM)
Universal Testing Machine
Shear Centre of Open Sections
Shear center is a point on the cross of the beam and the shear force passes through this point which causes the beam to bend without twisting. If the resultant of the internal shear force system and the applied shear force at any section do not coincide, a torque is developed and the section undergoes a twist. For the section not to twist, the applied shear force must pass through the shear center which is the centroid of the internal shear force system. The experimental setup is used to determine the shear center of ‘C’ section beam.
Shear center of an open section beam
Torsion of a Thin Walled Tube and Solid Shaft
Tubes and shafts are among the most commonly used structures in engineering and subjected to torque. The objective of this experiment is to determine the shear modulus of the material by measuring the angle of twist due to the torque applied on the tube/ Shaft.
Torsion of a thin walled tube
Digital torsion testing machine for solid shaft
Unsymmetrical Bending of Beam
The well-known flexure formula is based on elementary theory of bending of beams and it assumes that the load is always applied through one of the principal axes of the section. Though the applied load passes through shear centre of the section, the plane of bending and the plane of loading need not necessarily be the same unless the load passes along the principal axes. Therefore knowledge of the location of the principal axes is required. The experimental is used to determine the principal axes.
Unsymmetrical bending of beams
Compression Test on Column, Critical Buckling Loads – Southwell Plot
The need for materials with high strength to weight ratio in aircraft design has resulted in the use of slender structural components that fail more often by instability (buckling) than by excessive stress. The simplest example of such a structural component is slender column. The Southwell plot is a graphical method of determining experimentally a columns critical load. The technique can be used as a non-destructive testing of any structural elements that may fail by buckling.
Compression test on column
Spring testing setup – Stiffness of the spring
Stiffness is a measure of ability of the material to resist the deformation in response to an applied force. Generally spring stiffness is the force required to cause unit deflection. The spring testing setup is used to determine the stiffness of the spring.
Experimental setup to determine spring stiffness
UNMANNED AERIAL VEHICLES LABORATORY
The UAV Lab under the Aerospace Engineering division has drone fabrication and testing facilities, along with advanced simulation systems. This comprehensive setup enables the design, construction, and rigorous evaluation of UAVs. The lab is equipped with various tools for prototype development and performance analysis. Furthermore, it benefits from the expertise of two faculty members who hold DGCA-issued drone pilot licenses for the small category, ensuring adherence to regulatory standards and enhanced practical training for students. The lab serves as a hub for innovation, research, and hands-on learning in the rapidly evolving field of unmanned aerial vehicles.
Small Category Type Certified Drone
DGCA-approved Type Certified Garuda Kisan Drone
The Garuda Kisan Drone is an advanced agricultural UAV designed to aid farmers in modernizing their crop management techniques, this drone is equipped with precision technology for tasks such as aerial spraying, crop monitoring, and field mapping. The Garuda Kisan Drone features autonomous flight capabilities, allowing it to cover large areas efficiently and effectively. Its high-resolution cameras and sensors provide real-time data, enabling farmers to make informed decisions and optimize crop yields. This drone represents a significant step forward in smart agriculture, promoting sustainable farming practices and increasing productivity. Students gain hands-on experience in drone operation, UAV design, control systems, aerodynamics and data analysis. It serves as a hands-on educational tool for mastering drone technology and its applications in real-world scenarios.
Flight Simulator Facility
Flight Simulator
The Flight Simulator in the drone lab offers aerospace engineering students an immersive and interactive learning experience. Equipped with all cockpit controls, the simulator replicates real-world flight conditions, allowing students to practice and refine their piloting skills in a controlled environment. It features realistic flight dynamics, varied weather conditions, and diverse terrains, providing comprehensive training for different aircrafts and UAV operations. This simulator not only enhances students' understanding of aircraft/drone control and navigation but also aids in the study of flight mechanics, aerodynamics, and mission planning. By bridging theoretical knowledge and practical application, it prepares students for advanced UAV deployment and research.
Thrust Measuring Instrument
Thrust Measuring Instrument
The Thrust Measuring Instrument in the drone lab is a crucial tool for aerospace engineering students, enabling precise measurement of UAV engine thrust. This device provides accurate data on the force generated by drone propulsion systems, essential for performance analysis and optimization. Students use it to understand the relationship between thrust, power, and efficiency in various flight conditions. The instrument supports hands-on experimentation and validation of theoretical models, enhancing learning in propulsion mechanics and aerodynamics. By integrating this tool into their studies, students gain practical insights into the design and testing of more efficient and powerful UAVs.
3D Printing Facility
3D Printer
The FabForge 3D Printing Facility in the drone lab offers aerospace engineering students access to advanced additive manufacturing technology. This facility enables the rapid prototyping and fabrication of intricate UAV components, allowing for innovative design and quick iteration. It supports the creation of custom parts, enhancing students' hands-on experience in UAV construction and material science. By utilizing this facility, students can experiment with different materials and geometries, fostering creativity and improving their engineering skills. This plays a pivotal role in bridging the gap between theoretical concepts and practical application in UAV design and development.
PID Controller
PID controller with Balancing Setup
In industrial control systems, a PID controller is a device that regulates the temperature, flow, pressure, speed, and other process variables. The most accurate and reliable controllers for these applications are proportional integral derivative (PID) controllers, which employ a control-loop feedback mechanism to maintain the desired level of process variables. PID control is a widely used method for guiding a system towards a desired location or level. It is utilized in various chemical and scientific processes as well as in automation and control systems to regulate rotor speeds. PID control employs closed-loop control feedback to maintain the actual output of a process that is as close to the target or setpoint output as possible. A PID controller primarily regulates the speed of the drone rotor in a speed control system. It receives input from an accelerometer/gyro sensor and compares the actual speed to the setpoint or the desired control speed. The control element receives output from the PID controller.
Drone Fabrication
Drone Assembly
The Drone Fabrication and Assembly facility in the UAV lab is a cornerstone for aerospace engineering students, offering a hands-on environment for building and assembling UAVs. This facility is equipped with advanced tools and machinery for cutting, shaping, and joining various materials used in drone construction. Students learn to fabricate individual components and integrate them into fully functional drones, gaining practical skills in electronics, mechanics, and aerodynamics. The facility supports comprehensive training in the entire lifecycle of UAV development, from initial design and prototyping to final assembly and testing, preparing students for real-world challenges in drone engineering and innovation.
Subsonic wind tunnel
The subsonic wind tunnel features a test section with dimensions of 600 mm by 600 mm by 4000 mm, designed to achieve a maximum velocity of 45 m/s. With a contraction ratio of 9:1, the tunnel efficiently streamlines airflow, minimizing turbulence and enhancing flow uniformity. It is powered by a motor with a maximum output of 22 kW and can reach up to 1500 rpm. This wind tunnel is ideal for various aerodynamic testing and educational purposes, providing precise control of airflow for accurate experimentation in areas such as lift calculation, drag reduction, airflow visualization, and aerodynamic research.
Subsonic wind tunnel
Specifications:
- Test section 600x600 mm
- Length of the test section 4 meters
- Maximum test section velocity 45 m/s
- Contraction ratio 9:1
- Maximum power 22KW
- Maximum RPM:1500
- Diameter of the Propeller blade: 1.3m
- Turbulence level: Below 2%
Flow visualization in Subsonic wind tunnel: Flow past a) cylinder, b) cambered aerofoil and c) symmetric Aerofoil
Supersonic wind tunnel
The supersonic wind tunnel has a test section measuring 100 mm by 100 mm, capable of achieving Mach numbers from 1.5 to 3.5. It operates with a maximum stagnation pressure of 10 bar and allows for test durations of up to 20 seconds. The storage tank, with a volume of 14.14 cubic meters, can be pressurised to a maximum of 20 bar using two 20 HP compressors. This wind tunnel is designed for high-speed aerodynamic testing, enabling precise studies of supersonic flow behaviour and shock waves over various test specimens.
Supersonic wind tunnel
Specifications:
- Test section dimension 100X100 mm
- Range of Mach No:1.5 to 3.5
- Maximum Stagnation pressure: 10 bars
- Test duration: 20 sec. nominal
- Pressure measurement :16 port pressure scanner
- Volume of Pressure tank:14.14 m3
- Maximum Pressure storage capacity: 20 bars
- 20 hp Compressors-with air coolers and dryers
Supersonic wind tunnel test section
Flow visualization using Schlieren technique: Flow past Spike Nose
Open Jet facility
The blow-down type open jet facility is designed to reach a maximum Mach number of 2.5, making it ideal for high-speed aerodynamic testing. It can achieve a maximum stagnation pressure of 10 bar, providing robust testing conditions. The facility allows for a test duration of up to 100 seconds, offering sufficient time for detailed analysis of supersonic flow characteristics. This setup is particularly suited for studying the behavior of objects in high-speed airflows, shockwave interactions, and other supersonic phenomena.
Open Jet facility
Flow visualization using Schlieren technique: Flow past missile fin.
Specifications:
- Blow down type
- Maximum Mach No:2.5
- Maximum Stagnation pressure: 10 bars
- Test duration: 100 sec. nominal
- Pressure measurement :16 port pressure scanner
- Volume of Pressure tank:14.14 m3
- Maximum Pressure storage capacity: 20 bars
- 20 hp Compressors-with air coolers and dryers
- Nozzle exit diameter=25 mm (max.)
Open wind tunnel
The open wind tunnel, measuring 5 meters in length, features a tunnel diameter of 1 meter and achieves a maximum velocity of 12 m/s. It is designed to test the performance of wind turbine blades effectively. The power output is obtained using a 375-watt DC generator with a rated RPM of 500. This setup is ideal for optimizing blade designs, enhancing energy capture, and ensuring reliable performance in varying wind conditions, contributing to the development of more efficient and durable wind turbines.
Open wind tunnel
Specifications:
- Tunel diameter: 1 meter
- Length of the tunnel: 5 meters
- Maximum velocity: 12 m/s
- DC Generator: 375W
- Maximum RPM: 500
CESSNA 152
The Cessna 152 is an American two-seat, fixed tricycle gear, general aviation airplane, used primarily for flight training and personal use.
Using a Cessna 152 in an aerospace engineering program allows students to study flight mechanics and aerodynamics through practical demonstrations and data collection. It offers hands-on experience with aircraft systems and maintenance, enhancing their technical skills. The aircraft can be used for performance testing and modifications, providing a platform for research and innovation projects. Students can also gain first-hand piloting experience and learn safety and emergency procedures. Integrating the Cessna 152 into coursework and interdisciplinary projects enriches the educational experience by linking theory with real-world applications
General characteristics:
| Specification | Description |
| Model | CESSNA - 152 |
| Capacity | 2 seater |
| Wingspan | 33 ft 4 in (10.2 m) |
| Length | 24 ft 1 in (7.3 m) |
| Height | 8 ft 6 in (2.6 m) |
| Wing area | 160 ft² (14.9 m²) |
| Empty Weight | 1,081 lb (490 kg) |
| Max take-off Wt. | 1,670 lb (757 kg) |
| Max Range | 414nm (766km) |
| Service Ceiling | 14700ft (4480m) |
| Configuration | High Wing Vertical Tail |
| Engine Model | 1 x Lycoming 0235-L2C |
| Cylinder type | Horizontally Opposed |
| Cooling system | Air Cooled |
| Propeller model | MCCUELEY |
| Fuel | 100LL |
| Fuel Tank Capacity | 24.5 gallons (92.75 litres) |
AVIONICS LABORATORY
The Avionics lab in the department of Aerospace Engineering is equipped with
Communication protocol of MIL-STD-1553B data bus and ARINC-429 data bus wherein students are given the provision to practically demonstrate the same using lab view Software.
Experiments are carried on for measuring various avionic parameters like temperature, Acceleration, position, Velocity using thermocouple, Accelerometer, GPS and Anemometer.
Performance study of simulation using MATLAB on Van Guard Missile System and Autopilot Control systems and also carried out.
Measurement of temperature and humidity using LoRaWAN gateway is carried out wherein the LPS8 is an open source LoRaWAN Gateway. It bridges LoRa wireless network to an IP network via WiFi, Ethernet.
The lab is equipped with RTOS facility wherein students receive hands on experience to execute the written RTOS API based exercise on APPCOE IDE and to develop RTOS based application and interface with Raspberry Pi and Arduino from APPCOE.
Thus, the students are blended with project-based learning in a class room environment.
