Biography
Dr Ravichandran completed his DPhil in 2025 at the Thermofluids Institute in the University of Oxford. He completed his integrated MEng in Aeronautical Engineering at Imperial College London.
Most Recent Publications
The combined effects of large-scale roughness and mass injection in hypersonic flow
The combined effects of large-scale roughness and mass injection in hypersonic flow
Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling
Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling
Aerodynamic effects and heat flux augmentation of a transpiration cooled hypersonic sharp leading edge
Aerodynamic effects and heat flux augmentation of a transpiration cooled hypersonic sharp leading edge
Correction: Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge
Correction: Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge
Gas injection into second mode instability on a 7 degree cone at Mach 7
Gas injection into second mode instability on a 7 degree cone at Mach 7
Research Interests
He is currently working on upgrades to the Cold Driven Shock Tube (CDST) for combustion experiments using sustainable fuels, in partnership with the Centre of Excellence for Hybrid Thermal Propulsion Systems. His doctoral thesis focused on the design and testing of transpiration cooling for hypersonic vehicles.
Related Academics
Most Recent Publications
The combined effects of large-scale roughness and mass injection in hypersonic flow
The combined effects of large-scale roughness and mass injection in hypersonic flow
Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling
Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling
Aerodynamic effects and heat flux augmentation of a transpiration cooled hypersonic sharp leading edge
Aerodynamic effects and heat flux augmentation of a transpiration cooled hypersonic sharp leading edge
Correction: Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge
Correction: Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge
Gas injection into second mode instability on a 7 degree cone at Mach 7
Gas injection into second mode instability on a 7 degree cone at Mach 7
