The major experimental facility includes:
Low Speed Subsonic Wind Tunnel
It is a subsonic wind tunnel with maximum velocity of upto 60 m/sec in the rectangular test section of size 0.6m x 0.9m. It is used for measurement of pressure distribution over airfoils, determination of boundary layer over flat plate, flow visualization over delta wing model etc.
Specifications:
| Velocity Range | upto 60 m/s |
| Test Section | 0.6m x 0.9m x 2m (HxWxL) |
| Max. Reynolds number | ~4x106 (with tunnel width as characteristic Length) |
| Turbulence intensity | <1% |
| Instruments | CTA Hot Wire Anemometer System with different probes and dedicated data acquisition and processing system, 32 channel Pressure transducers system with Data Acquisition and Processing unit, U-tube manometer, Multi-tube manometer, Load Cells |
| Software | Labview, Streamware |
Smoke Tunnel
A dedicated smokel tunnel facility is available which is used for smoke flow visualization over airfoils, cylinders and other body shapes.
Low speed Blow Type Wind Tunnel
A blower type wind tunnel is available which allows testing of aircraft components in open test-section thereby providing flexibility in size of the model being tested.
Supersonic Open-jet Wind Tunnel
An intermittent blow-down type open-jet wind tunnel is available which enables experiments in the area of compressible aerodynamics. The tunnel is well equipped with instruments like pressure transducers, Data acquisition & processing system, Schlieren System to acquire and analyze the data.
Specifications:
| Tunnel Type | Blow-down type intermittent |
| Suitable Velocity Range | 100m/s and more with upto 2.5 Mach number |
| Run time | ~45 s at 2.5 M |
| Storage tank specifications | 15000 m3 at 10 bar |
| Test section | 4 cm x 4 cm square test section |
| Instruments | Data Acquisition and Processing unit, Pressure transducer, Schlieren System |
| Software | Labview, MatLab, Octave |
Reddy-Shock Tube
Hand driven Reddy shock-tube allows flow with velocity upto Mach 10. The experimental setup allows to study aerodynamic characteristics of different bodies at Hypersonic mach numbers. The impact of temperature variation on shock speed can also be studied in this setup.
