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Please use this identifier to cite or link to this item: http://hdl.handle.net/2005/1120

Title: Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration
Authors: Hima Bindu, V
Advisors: Reddy, K P J
Saravanan, S
Keywords: Aerothermodynamics
Scramjet Engines
Hypersonic Flows
Convective Heat Transfer
Aerodynamic Heating
Aerodynamic Forces
Hypersonic Shock Tunnel
Aerodynamic Measurements
Combustion Chambers - Heat Transfer
Accelerometer
Hypersonic Flow
Hypersonic Vehicles
Submitted Date: Nov-2009
Series/Report no.: G23526
Abstract: The recent resurgence in hypersonics is centered around the development of SCRAMJET engine technology to power future hypersonic vehicles. Successful flight trials by Australian and American scientists have created interest in the scramjet engine research across the globe. To develop scramjet engine, it is important to study heat transfer effects on the engine performance and aerodynamic forces acting on the body. Hence, the main aim of present investigation is the design of scramjet engine configuration and measurement of aerodynamic forces acting on the model and heat transfer rates along the length of the combustor. The model is a two-dimensional single ramp model and is designed based on shock-on-lip (SOL) condition. Experiments are performed in IISc hypersonic shock tunnel HST2 at two different Mach numbers of 8 and 7 for different angles of attack. Aerodynamic forces measurements using three-component accelerometer force balance and heat transfer rates measurements using platinum thin film sensors deposited on Macor substrate are some of the shock tunnel flow diagnostics that have been used in this study.
URI: http://hdl.handle.net/2005/1120
Appears in Collections:Aerospace Engineering (aero)

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