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Aero-Thermo-Structural Analysis of Inlet for Rocket Based Combined Cycle EnginesNASA has been developing advanced space transportation concepts and technologies to make access to space less costly. One such concept is the reusable vehicles with short turn-around times. The NASA Glenn Research Center's concept vehicle is the Trailblazer powered by a rocket-based combined cycle (RBCC) engine. Inlet is one of the most important components of the RBCC engine. This paper presents fluid flow, thermal, and structural analysis of the inlet for Mach 6 free stream velocity for fully supersonic and supercritical with backpressure conditions. The results concluded that the fully supersonic condition was the most severe case and the largest stresses occur in the ceramic matrix composite layer of the inlet cowl. The maximum tensile and the compressive stresses were at least 3.8 and 3.4, respectively, times less than the associated material strength.
Document ID
20010012170
Document Type
Conference Paper
Authors
Shivakumar, K. N.
(North Carolina Agricultural and Technical State Univ. Greensboro, NC United States)
Challa, Preeti
(North Carolina Agricultural and Technical State Univ. Greensboro, NC United States)
Sree, Dave
(Tuskegee Inst. AL United States)
Reddy, Dhanireddy R.
Date Acquired
August 20, 2013
Publication Date
August 1, 2000
Publication Information
Publication: HBCUs/OMUs Research Conference Agenda and Abstracts
Subject Category
Spacecraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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