Hypersonic Air Flow with Finite Rate Chemistry
Abstract
In this report, we present the results of a number of experimental studies and the accompanying analyses to develop and refine prediction techniques and the models that are employed in them to describe the effects of non-equilibrium flow chemistry, shock interaction, and turbulent mixing and combustion on the performance of vehicles and air breathing engines designed to fly in the hypersonic flow regime at velocities greater than 2 km/sec. During this research program, experimental studies and analyses were conducted to: (1) Define and predict the vibrational and chemical nonequilibrium characteristics of hypervelocity flows developed in a contoured nozzle. (2) Evaluate and compute the effects of real-gas chemistry on the characteristics and properties of base flows, interaction regions resulting from shock wave/boundary layer interaction and shock/shock interaction over simple model configurations, and indented nose shapes. (3) Study the characteristics of high-temperature regions of turbulent mixing and combustion associated with scramjet operations at Mach 12. The report is divided into four sections, each of which covers separate but inter-related experimental and theoretical programs that were conducted during the present contract.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1997
- Accession Number
- ADA388086
Entities
People
- Daniel A. Erwin
- E. Phillip Muntz
- Ian D. Boyd
- Ronald K. Hansen
Organizations
- University of Southern California