An inlet system is being tested to evaluate methodologies for a
turbine based combined cycle propulsion system to perform a
controlled inlet mode transition. Prior to wind tunnel based
hardware testing of controlled mode transitions, simulation models
are used to test, debug, and validate potential control algorithms.
One candidate simulation package for this purpose is the High Mach
Transient Engine Cycle Code (HiTECC). The HiTECC simulation package
models the inlet system, propulsion systems, thermal energy,
geometry, nozzle, and fuel systems. This paper discusses the
modification and redesign of the simulation package and control
system to represent the NASA large-scale inlet model for Combined
Cycle Engine mode transition studies, mounted in NASA Glenn s 10-
by 10-Foot Supersonic Wind Tunnel. This model will be used for
designing and testing candidate control algorithms before
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