Client
NASA
Project Objectives
- Simulate the mixing and shear layer development between supersonic flows of fuel and air downstream of a splitter plate that would be used in the National Aerospace Plane Combustor (NASP)
- The main stumbling block of the National Aerospace Plane was how to achieve supersonic combustion of a liquid hydrocarbon fuel and atmospheric air. A variety of shear layer techniques, vortex dynamics, and shock enhanced mixing strategies were examined to enhance the mixing rate of fuel and air before the reactants exited the combustor.
Summary of Project and Results (Non-Confidential)
- Developed the Initial Conditions and Boundary Conditions for the simulation
- Meshed the shear layer flowfield
- Used a NASA LEWIS Navier-Stokes solver to perform the simulations
- Computed the mixing rates and combustion potentials for a variety of mixing enhancement strategies
Vorticity Contours produced by the Numerical Simulation of a Three Dimensional Reacting Planar Jet