Laboratories

The department has the following Laboratories:

  • Wind Tunnel Facility
  • High Enthalpy and Propulsion Laboratory
  • Aircraft Structures Laboratory
  • Avionics Laboratory
  • CESSNA 152


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



At our Avionics Lab, we are to impart the Microprocessor Programming and Avionics practical knowledge by measuring various avions parameters like temperature, Acceleration, position, Velocity using thermocouple, Accelerometer, GTRO, Anemometer for students. We provide some Performance study of simulation using MATLAB practical study on Van Guard Missile System, Autopilot Control systems and practical study over GPS & MIL data bus for the students and researchers.

Avionics Laboratory


Avionics Laboratory

FacilitiesCapabilities
8085 Processor kitProgramming (Assembly language)
8086 Processor kitProgramming (Assembly language)
Temperature measurementUsing RTD Setup
Temperature measurementUsing Thermocouple setup
Acceleration measurementUsing Accelerometer
Position/Angular MeasurementUsing GYRO
Velocity measurementUsing Hot wire Anemometer
Van Guard Missile systemPerformance study using MATLAB
Autopilot control systemPerformance study using MATLAB
GPSStudy experiment
Communication protocol of MIL STD 1553B Data BusStudy experiment

At our Avionics Lab, we are to impart the Microprocessor Programming and Avionics practical knowledge by measuring various avions parameters like temperature, Acceleration, position, Velocity using thermocouple, Accelerometer, GTRO, Anemometer for students. We provide some Performance study of simulation using MATLAB practical study on Van Guard Missile System, Autopilot Control systems and practical study over GPS & MIL data bus for the students and researchers.

CESSNA-152

General characteristics:

SpecificationDescription
ModelCESSNA - 152
Capacity2 seater
Wingspan33 ft 4 in (10.2 m)
Length24 ft 1 in (7.3 m)
Height8 ft 6 in (2.6 m)
Wing area160 ft² (14.9 m²)
Empty Weight1,081 lb (490 kg)
Max take-off Wt.1,670 lb (757 kg)
ConfigurationHigh Wing Vertical Tail
Engine Model1 x Lycoming 0235-L2C
Cylinder typeHorizontally Opposed
Cooling systemAir Cooled
Propeller modelMCCUELEY
Fuel100LL