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Research - Aerospace Propulsion
Rocket Propulsion and Solid Propellant Combustion
Airbreathing Propulsion and Combustion
Cascade Flows
Multiphase Flow Simulation
Combustion Instability
Optical Flow/Combustion Diagnostics
Facilities Available
Window bomb
A cylinderical combustion chamber
Ability to handle elevated pressure upto 150 bar
facility to visualize and record propellant combustion with external illumination
Erosive burning facility
Capablity of burning solid propellant under high mach number(including supersonic) cross flow conditions
Detection of burning rate chnages under different cross-flow conditions, using high speed photography
Static solid rocket motor test facility
Capability of burning 80 gm of solid propellant within one second
Provision to test nozzleless solid rocket motor configuration, solid fuel ramjets and hybrid rocket motors
Gelled liquid propellant rocket motor static test facility
To study the injection characteristics and atomization of impinging jets involving gelled propellants
It is the bench mark for developing rocket motor thrust chambers
Diagnostic techniques
Thrust calculation for supersonic combustor by load cell
Thermal measurements
Thin film guages for heat transfer studies
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