Laser Based Directed Energy Systems for Flow Control in Hypersonic Inlet Applications
Abstract
A significant progress in the design of high speed vehicles has been achieved over the past several decades [1][2][3]. However one of the critical design issues remain unresolved are efficient propulsion system. This research is focusing on improving the performance of the scramjets engine through the active flow control at the inlet. Typically, flow control in supersonic inlet involved variable geometry apparatus such as that used on Rolls Royce/Snecma Olympus engine system for Concorde. Although this approach is adequate, the inherent inertia in such mechanical devices limits their effectiveness in engine control at high speeds. These studies confirmed that pulsed laser energy deposition can be used for drag reduction and flow separation and also increase the pressure recovery at supersonic flow. However, at the hypersonic flow none of the previous study attempt to investigate the effect of laser energy deposition on drag and flow separation and the physics behind that.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 21, 2022
- Source ID
- FA23862114016XX0
Entities
People
- Mohd Rosdzimin Abdul Rahman
Organizations
- Air Force Office of Scientific Research
- National Defence University of Malaysia
- United States Air Force