Study of Premixed, Shock-Induced Combustion With Application to Hypervelocity Flight
Study of Premixed, Shock-Induced Combustion With Application to Hypervelocity Flight
- New search for: E. L. Axdahl
- New search for: E. L. Axdahl
One 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 information
Study of Premixed, Shock-Induced Combustion With Application to Hypervelocity Flight
2013
245 pages
Report
No indication
English
Fluid Mechanics , Space Technology , Aircraft , Premixing , Supersonic combustion ramjet engines , Dynamic models , Velocity , Shock waves , Ignition , Mach number , Spontaneous combustion , Combustion chambers , Fuel injection , Engine design , Hypervelocity flow , Propulsion system configurations , Hypersonic flight , Film cooling , Altitude , Systems simulation , Performance tests , Computational fluid dynamics
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