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Ramaswamy, Deepak Prem, M.Sc.
Phone:+49 241 80 90398
Fax:+49 241 80 92257
Email:
Raum:103


Allgemeine Informationen:

Career Highlights:

2018 - Present Research Assistant Institute of Aerodynamics, RWTH Aachen University
2017 MSc Aerospace Engineering Delft University of Technology, The Netherlands.
2015 BE Aeronautical Engineering Anna University, Chennai.

Research Interests:

  • Compressible Flows
  • Shock wave / Boundary layer Interaction
  • Flow control
  • Experimental Methods


Projekte:
  • Separation control with Air Jet Vortex Generator arrays in transonic and supersonic flow



Angebotene Bachelorarbeiten:
01.07.2019Separation control with air-jet vortex generators in a shock-wave / turbulent boundary layer interactionInfoblatt herunterladen

Flow fields around high speed vehicles are characterised by frequent occurrence of shock wave / boundary layer interactions. A strong shock wave imposes a large adverse pressure gradient on the boundary layer and can induce large scale separation. This interaction can lead to high local fluctuating pressure and thermal loads detrimental to the vehicle structure. Hence, effective control of these phenomena is necessary for cheaper and more efficient air and space transportation. A promising approach is based on the injection of air jets into the boundary layer. The streamwise vortices generated by these air-jets redistribute the momentum within the boundary layer, making it more resistant to separation. The effectiveness of air-jet vortex generators in mitigating flow separation has been verified in subsonic, transonic and supersonic flow conditions. However, further studies are essential to understand the underlying governing mechanism. In the framework of this proposed thesis, state-of-the-art experimental techniques will be employed to study the influence of air-jet vortex generators on shock wave / turbulent boundary layer interactions.



Angebotene Masterarbeiten:
01.07.2019Separation control with air-jet vortex generators in a shock-wave / turbulent boundary layer interactionInfoblatt herunterladen

Flow fields around high speed vehicles are characterised by frequent occurrence of shock wave / boundary layer interactions. A strong shock wave imposes a large adverse pressure gradient on the boundary layer and can induce large scale separation. This interaction can lead to high local fluctuating pressure and thermal loads detrimental to the vehicle structure. Hence, effective control of these phenomena is necessary for cheaper and more efficient air and space transportation. A promising approach is based on the injection of air jets into the boundary layer. The streamwise vortices generated by these air-jets redistribute the momentum within the boundary layer, making it more resistant to separation. The effectiveness of air-jet vortex generators in mitigating flow separation has been verified in subsonic, transonic and supersonic flow conditions. However, further studies are essential to understand the underlying governing mechanism. In the framework of this proposed thesis, state-of-the-art experimental techniques will be employed to study the influence of air-jet vortex generators on shock wave / turbulent boundary layer interactions.



Letztes Update: 11:05:42 - 01.07.2019

 
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