Date of Award

Spring 2014

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

Dr. William A. Engblom

First Committee Member

Dr. Reda Mankbadi

Abstract

A Reynolds-averaged Navier-Stokes computational model featuring a mixing-limited, quasi-global chemical kinetics approach for an ethylene-methane fuel mixture is described and used in a validation effort against the Hypersonic International Flight Research Experimentation (HIFiRE) Direct Connect Rig experimental data for flight Mach numbers of 5.84, 6.5, and 8.0. An average error level between the numerical predictions and corresponding experimental measurements for static pressure along the engine flowpath is found to be within approximately 10%, for the two lowest Mach number cases, without calibration. Key features of the numerical flowfield development are identified, including regions within the combustor found to be significantly mixing-limited for each fuel type. The sensitivity of the results to turbulent Schmidt is also briefly examined.

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