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Articles 1 - 5 of 5
Full-Text Articles in Engineering
A Performance Analysis Of A Rocket Based Combined Cycle (Rbcc) Propulsion System For Single-Stage-To-Orbit Vehicle Applications, Nehemiah Joel Williams
A Performance Analysis Of A Rocket Based Combined Cycle (Rbcc) Propulsion System For Single-Stage-To-Orbit Vehicle Applications, Nehemiah Joel Williams
Masters Theses
Rocket-Based Combined Cycle (RBCC) engines combine the best performance characteristics of air-breathing systems such as ramjets and scramjets with rockets with the goal of increasing payload/structure and propellant performance and thus making LEO more readily accessible. The idea of using RBCC engines for Single-Stage-To-Orbit (SSTO) trans-atmospheric acceleration is not new, but has been known for decades. Unfortunately, the availability of detailed models of RBCC engines is scarce. This thesis addresses the issue through the construction of an analytical performance model of an ejector rocket in a dual combustion propulsion system (ERIDANUS) RBCC engine. This performance model along with an atmospheric …
Evaluation Of Geometric Scale Effects For Scramjet Isolators, Jaime Enrique Perez
Evaluation Of Geometric Scale Effects For Scramjet Isolators, Jaime Enrique Perez
Masters Theses
A numerical analysis was conducted to study the effects of geometrically scaling scramjet inlet-combustor isolators. Three-dimensional fully viscous numerical simulation of the flow inside constant area rectangular ducts, with a downstream back pressure condition, was analyzed using the SolidWorks Flow Simulation software. The baseline, or 1X, isolator configuration has a 1” x 2.67” cross section and 20” length. This baseline configuration was scaled up based on the 1X configuration mass flow to 10X and 100X configurations, with ten and one hundred times the mass flow rate, respectively. The isolator aspect ratio of 2.67 was held constant for all configurations. To …
A General Simulation Of An Air Ejector Diffuser System, Derick Thomas Daniel
A General Simulation Of An Air Ejector Diffuser System, Derick Thomas Daniel
Masters Theses
A computer model of a blow-down free-jet hypersonic propulsion test facility exists to validate facility control systems as well as predict problems with facility operation. One weakness in this computer model is the modeling of an air ejector diffuser system. Two examples of facilities that could use this ejector diffuser model are NASA Langley Research Center's 8-ft High Temp. Tunnel (HTT) and the Aero-Propulsion Test Unit (APTU) located at Arnold Engineering Development Center. Modeling an air ejector diffuser system for a hypersonic propulsion test facility includes modeling three coupled systems. These are the ejector system, the primary free-jet nozzle that …
Nonlinear Acoustics Of Piston-Driven Gas-Column Oscillations, Andrew William Wilson
Nonlinear Acoustics Of Piston-Driven Gas-Column Oscillations, Andrew William Wilson
Masters Theses
The piston-driven oscillator is traditionally modeled by directly applying boundary conditions to the acoustic wave equations; with better models re-deriving the wave equations but retaining nonlinear and viscous effects. These better models are required as the acoustic solution exhibits singularity near the natural frequencies of the cavity, with an unbounded (and therefore unphysical) solution. Recently, a technique has been developed to model general pressure oscillations in propulsion systems and combustion devices. Here, it is shown that this technique applies equally well to the piston-driven gas-column oscillator; and that the piston experiment provides strong evidence for the validity of the general …
Theoretical Models For Wall Injected Duct Flows, Tony Saad
Theoretical Models For Wall Injected Duct Flows, Tony Saad
Doctoral Dissertations
This dissertation is concerned with the mathematical modeling of the flow in a porous cylinder with a focus on applications to solid rocket motors. After discussing the historical development and major contributions to the understanding of wall injected flows, we present an inviscid rotational model for solid and hybrid rockets with arbitrary headwall injection. Then, we address the problem of pressure integration and find that for a given divergence free velocity field, unless the vorticity transport equation is identically satisfied, one cannot find an analytic expression for the pressure by direct integration of the Navier-Stokes equations. This is followed by …