A Study of Premixed, Shock-Induced Combustion With Application to Hypervelocity FlightOne of the current goals of research in hypersonic, airbreathing propulsion is access to higher Mach numbers. A strong driver of this goal is the desire to integrate a scramjet engine into a transatmospheric vehicle airframe in order to improve performance to low Earth orbit (LEO) or the performance of a semiglobal transport. An engine concept designed to access hypervelocity speeds in excess of Mach 10 is the shock-induced combustion ramjet (i.e. shcramjet). This dissertation presents numerical studies simulating the physics of a shcramjet vehicle traveling at hypervelocity speeds with the goal of understanding the physics of fuel injection, wall autoignition mitigation, and combustion instability in this flow regime.
Document ID
20150001229
Acquisition Source
Langley Research Center
Document Type
Thesis/Dissertation
Authors
Axdahl, Erik L. (Georgia Inst. of Tech. Atlanta, GA, United States)
Date Acquired
February 3, 2015
Publication Date
December 1, 2013
Subject Category
Spacecraft Propulsion And PowerFluid Mechanics And ThermodynamicsAircraft Propulsion And Power