High Performance Computing in the SCRamjet Design Project HPC User Forum Meeting Roanoke, April /21/091 Chris Larson, Axel Dietrich

04/21/092 combustion occurs at supersonic speeds no moving parts no on-board oxidizer A Scramjet is an air-breathing propulsion system, developed to operate in the hypersonic region of flight Project Mission Goal is to design a flight-capable Scramjet engine

04/21/093 The design process incorporated different state of the art computer software

04/21/094 Flow properties throughout engine cycle determined using isentropic flow equations and STANJAN InletIsolatorCombustorNozzle T 01 P 01 T 02 P 02 T 03 P 03 T 04 P 04 T 05 P 05 T 1 P 1 T 5 P 5 Mach 5 Air Cavity, injection, torch Mach 2 STANJAN software used to model combustion process in Scramjet engine Combustor split into ten different sections, each in which hydrogen is injected, in order to more accurately model combustion process

Isolator 04/21/095 CAD models of Scramjet engine components developed using NX 6 Engine component geometries dependent on flow properties throughout Scramjet, and initial constraints on isolator and combustor inlet geometry Combustor Nozzle

CFD model has been generated in order to simulate the flow conditions in the combustor 04/21/09 6 Free Stream Model of the combustor containing the cavity CFD Model of the combustor section designed in GAMBIT 2.4

CFD simulation validated predicted combustor flow conditions exited by the Cavity 04/21/09 7 Distribution of mach number simulated by FLUENT 6.3

CFD simulation validated predicted combustor flow conditions exited by the Cavity 04/21/09 8 Distribution of static temperature simulated by FLUENT 6.3

04/21/099 To simulate wind tunnel testing conditions, a more detailed CFD simulation was started Insert plate that will be used for wind tunnel testing GAMBIT model of insert plate GAMBIT model was divided into 9 sections to apply different types of meshes