Rapidly Expanding Non Equilibrium Hypersonic Flow
Abstract
The aim of this proposal is to perform experiments on a simplified two dimensional geometrical configuration which reproduces that part of the flow where the biggest uncertainties lie - the expansion fan that couples the windward and the leeward surfaces. In this non equilibrium region of rapidly falling temperature and pressure, recombination processes start to occur, and vibrational and electronic temperatures depart significantly from the translational temperature. By studying these effects in a simple configuration decoupled from the macroscopic details of a complex flow field, we will be better able to understand and model the fundamental mechanisms involved. This will subsequently allow improved physical models to be incorporated into numerical simulations of the full flow field, and the heating environment experienced by hypersonic vehicles to be defined with improved accuracy.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Sep 21, 2018
- Source ID
- FA23861614057
Entities
People
- Richard Morgan
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Queensland