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An improved analytical model of the separated region on nozzle boattailsA viscous flow calculation is formulated for modelling the effects of separated, reverse flow regions on nozzle afterbody pressures and drags at subsonic Mach numbers. A discriminating streamline approach is used. Effects of skin friction, axial pressure gradient, and nozzle jet entrainment on the separated discriminating streamline shape are included. The viscous flow calculation is coupled to a potential flow calculation. The combined analysis is found to accurately predict both the magnitude of the measured afterbody pressures and drag, and also their variation with Reynolds number, Mach number and afterbody shape.
Document ID
19780059633
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Presz, W. M., Jr. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Buteau, J. D. (United Technologies Corp. Pratt and Whitney Aircraft Group, East Hartford, Conn., United States)
King, R. W. (United Technologies Corp. Chemical Systems Div., Sunnyvale, Calif., United States)
Putnam, L. E. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 78-995
Meeting Information
Meeting: Joint Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: July 25, 1978
End Date: July 27, 1978
Sponsors: Society of Automotive Engineers, American Institute of Aeronautics and Astronautics
Accession Number
78A43542
Funding Number(s)
CONTRACT_GRANT: NAS1-14462
Distribution Limits
Public
Copyright
Other

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