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Advanced Methods for Aircraft Engine Thrust and Noise Benefits: Nozzle-Inlet Flow AnalysisThe research is focused on a wide regime of problems in the propulsion field as well as in experimental testing and theoretical and numerical simulation analyses for advanced aircraft and rocket engines. Results obtained are based on analytical methods, numerical simulations and experimental tests at the NASA LaRC and Hampton University computer complexes and experimental facilities. The main objective of this research is injection, mixing and combustion enhancement in propulsion systems. The sub-projects in the reporting period are: (A) Aero-performance and acoustics of Telescope-shaped designs. The work included a pylon set application for SCRAMJET. (B) An analysis of sharp-edged nozzle exit designs for effective fuel injection into the flow stream in air-breathing engines: triangular-round and diamond-round nozzles. (C) Measurement technique improvements for the HU Low Speed Wind Tunnel (HU LSWT) including an automatic data acquisition system and a two component (drag-lift) balance system. In addition, a course in the field of aerodynamics was developed for the teaching and training of HU students.
Document ID
20030063107
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Morgan, Morris H.
(Hampton Univ. VA, United States)
Gilinsky, Mikhail
(Hampton Univ. VA, United States)
Patel, Kaushal
(Hampton Univ. VA, United States)
Coston, Calvin
(Hampton Univ. VA, United States)
Blankson, Isaiah M.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 21, 2013
Publication Date
February 1, 2003
Publication Information
Publication: HBCUs/OMUs Research Conference Agenda and Abstracts
Subject Category
Spacecraft Design, Testing And Performance
Funding Number(s)
CONTRACT_GRANT: CRDF-RE1-2068
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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