NDLI: Thermostructural analysis of simulated cowl lips

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Thermostructural analysis of simulated cowl lips

Content Provider	NASA Technical Reports Server (NTRS)
Author	Melis, Matthew E.
Copyright Year	1988
Description	Three dimensional finite element analyses using MSC/NASTRAN and MARC are performed to predict the thermal and structural response of various cooling schemes under high heat loads. Steady state heat transfer analyses and elastic stress analyses are performed using MSC/NASTRAN. Elastic/plastic analyses are done using MARC. To help verify these analyses experimentally, a hydrogen-oxygen rocket engine was modified to use the exhaust stream as a high enthalpy, high heat flux source to evaluate various actively cooled, simulated cowl lip (leading edges) segments as well as flat structural segments. Cross flow and parallel flow cooling configurations were tested and analyzed using cooling fluids of water and gaseous hydrogen. In addition, various material types, including high conductivity copper, nickel, and a copper and graphite metal matrix composite were tested and compared.
File Size	2369423
Page Count	10
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880013019
Archival Resource Key	ark:/13960/t28963d38
Language	English
Publisher Date	1988-05-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Finite Element Method Cooling Cowlings Thermodynamic Efficiency Flow Distribution Inlet Nozzles Inelastic Stress Nastran Leading Edges Thermal Stresses Heat Flux Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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