Effects of Focused Energy Deposition on the Performance of Hypersonic Nozzle Flow
Department
Mechanical and Aerospace Engineering
Major
Aerospace Engineering
Research Advisor
Riggins, David W.
Advisor's Department
Mechanical and Aerospace Engineering
Funding Source
UMR Opportunities for Undergraduate Research Experiences (OURE)
Abstract
A numerical analysis of the effects of focused energy deposition in the flow of a two-dimensional hypersonic nozzle at Mach 10 is presented. Computational Fluid Dynamics software modeling the full Navier-Stokes equations is used. Thrust, pressure, and temperature effects caused by the energy deposition inside the nozzle are shown. Increased quantities of energy deposited in the flow field create pressure distributions within the flow and along the nozzle boundaries that vary from the case in which no energy is deposited. The primary analysis focuses on the case where the maximum amount of energy is deposited into the flow while staying below the maximum temperature allowed by the simulation program. It is shown that thrust is considerably increased by the addition of focused energy to the flow. This energy deposition theory may lead to further improvements in the design of hypersonic nozzles to increase thrust and propulsion system efficiency and flexibility.
Biography
Natalie Frenz is a junior in aerospace engineering, also pursuing a minor in Spanish.. She is Vice-President 1 of the UMR chapter of the Society of Women Engineers, a member of the American Institute of Aeronautics and Astronautics and the Society of Flight Test Engineers. Natalie is also a member of several honor societies, including Phi Eta Sigma, Tau Beta Pi, Kappa Mu Epsilon, and Sigma Gamma Tau, the aerospace engineering honor society.
Research Category
Engineering
Presentation Type
Poster Presentation
Document Type
Poster
Presentation Date
12 Apr 2006, 1:00 pm
Effects of Focused Energy Deposition on the Performance of Hypersonic Nozzle Flow
A numerical analysis of the effects of focused energy deposition in the flow of a two-dimensional hypersonic nozzle at Mach 10 is presented. Computational Fluid Dynamics software modeling the full Navier-Stokes equations is used. Thrust, pressure, and temperature effects caused by the energy deposition inside the nozzle are shown. Increased quantities of energy deposited in the flow field create pressure distributions within the flow and along the nozzle boundaries that vary from the case in which no energy is deposited. The primary analysis focuses on the case where the maximum amount of energy is deposited into the flow while staying below the maximum temperature allowed by the simulation program. It is shown that thrust is considerably increased by the addition of focused energy to the flow. This energy deposition theory may lead to further improvements in the design of hypersonic nozzles to increase thrust and propulsion system efficiency and flexibility.
Comments
Joint project with John Gantt