Combustion driven shock tunnel: Flows can be generated at Mach number ranges between 5-12 with Enthalpy levels upto 6 MJ. Both reflected and straight modes are possible, and can be used to study moving shock problems.

Supersonic wind tunnels: Free jet facility that can operate at supersonic speeds ranging from Mach number of 1.5-3.6

Compressor: A 2-stage reciprocating water cooled type compressor operated by a 90 kW motor with a maximum discharge of about 510 m3/hour

Supersonic combustion facility

Facility for oscillatory combustion response of premixed flames

Instruments

• CCD camera
• Laser
• Light sources, optical mirrors and lenses
• Piezo-electric and piezo-resistive type pressure transducers
• Platinum-Rhodium thermocouple for flame temperature in supersonic combustion
• Pitot and static probes

Low density tunnel: Only one of its kind in South-East Asia and can simulate high altitude flow conditions covering continuum to transitional flow regimes.

Transonic wind tunnel: Induction type self-correcting tunnel that can operate at a Mach number range of 0.8-1.2

Air reservoirs: Three reservoirs with a capacity of 12 m3, with maximum pressure of 1750 kN/m2 Strut based mixing enhancement facility: Operates at supersonic mach number with the option to change test sections

Cavity based flame holding facility

Diagnostic Techniques and Instruments

• Particle image velocimetry
• Doubled pulsed laser with power supplying unit
• Three-Component Phase Doppler Particle Analyzer
• Mixing studies by planar mie-scattering technique flow field studies in supersonic flow by schlieron and shadowgraph methods
• Glow discharge visualization of low density free jets
• Interferometric methods for shear stress measurements in low density jet impingement
• Acetone and Iodine PILF for mixing concentration measurements
• Spray PLIF for volume and spatial diameter distribution