NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-pipe ShroudsInvestigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
Document ID
19930082151
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
External Source(s)
hdl:100.2/ADA800670
Authors
Ellerbrock, Herman H. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Wcislo, Chester R. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Dexter, Howard E. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 16, 2013
Publication Date
December 1, 1947
Subject Category
Aerodynamics
Report/Patent Number
NACA-TN-1495
Accession Number
93R11441
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
HEAT EXCHANGERS, SHROUDED
MANIFOLDS, EXHAUST - COOLING SHROUDS
HEAT EXCHANGERS, EXHAUST - PRESSURE DROP
EQUATIONS - HEAT TRANSMISSION
HEAT TRANSMISSION - ENGINES, JET
ENGINES, JET - COOLING
FLOW OF GASES - PIPES
ENGINES - COOLING, EXHAUST-GAS
EXHAUST PIPES, TAIL - COOLING
EXHAUST GASES - TEMPERATURE

Related Records

There are no records associated with this record.
No Preview Available