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Prediction of subsonic aircraft flows with jet exhaust interactionsA numerical procedure to calculate the flow fields resulting from the viscous inviscid interactions that occur when a strong jet exhaust and aircraft flow field coupling exists was developed. The approach divides the interaction region into zones which are either predominantly viscous or inviscid. The flow in the inviscid zone, which surrounds most of the aircraft, is calculated using an existing potential flow code. The viscous flow zone, which encompasses the jet plume, is modeled using a parabolized Navier-Stokes code. The procedure features the coupling of the zonal solutions such that sufficient information is transferred between the zones to preserve the effects of the interactions. The zonal boundaries overlap and the boundary conditions are the information link between zones. An iteration scheme iterates the coupled analysis until convergence has been obtained.
Document ID
19820005223
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roberts, D. W.
(Boeing Military Airplane Development Seattle, WA, United States)
Date Acquired
August 10, 2013
Publication Date
September 1, 1981
Publication Information
Publication: AGARD Aerodyn. of Power Plant Installation
Subject Category
Aerodynamics
Accession Number
82N13096
Funding Number(s)
CONTRACT_GRANT: NAS2-10100
Distribution Limits
Public
Copyright
Other
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