SHOCK-WAVE - BOUNDARY LAYER INTERACTION CONTROL IN MACH 5 HYPERSONIC FLOW USING COMBINED ACTIVE FLOW CONTROL
Abstract
Shock wave-boundary layer interaction (SBLI) is an undesirable phenomenon occurring in re-entry vehicles from outer space and high-speed air-breathing propulsion systems including hypersonic aircrafts. This stimulates boundary layer separation due to adverse pressure gradients which consequently lead to flow distortion engine failure. Hence it is essential to apply flow control mechanisms to prevent the occurrence of such phenomena. This study involves a mechanism to control boundary layer separation by combining three active flow control techniques; plasma discharge, jet and suction. The combined active flow control techniques will be investigated experimentally by National Defence University of Malaysia (UPNM) researchers using the hypersonic wind tunnel facilities (Mach 5) at The University of Manchester. State-of-the-art flow diagnostics tools such as Particle Image Velocimetry (PIV), Pressure Sensitive Paints (PSP) and high-speed schlieren will be employed in the project. From this study, optimised designs and configurations of the combined active flow control mechanism will be obtained, which will contribute to the design of future high-speed air-breathing propulsion system and re-entry vehicles that delivers better performance. Understanding the SBLI phenomenon and the control methods will also reduce the risk of accidents associated with both space and high-speed air-breathing vehicles.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- May 10, 2022
- Source ID
- FA23862114010XX0
Entities
People
- Mohd Rashdan Saad
Organizations
- Air Force Office of Scientific Research
- National Defence University of Malaysia
- United States Air Force