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On the Solution of the Three-Dimensional Flowfield About a Flow-Through NacelleThe solution of the three dimensional flow field for a flow through nacelle was studied. Both inviscid and viscous inviscid interacting solutions were examined. Inviscid solutions were obtained with two different computational procedures for solving the three dimensional Euler equations. The first procedure employs an alternating direction implicit numerical algorithm, and required the development of a complete computational model for the nacelle problem. The second computational technique employs a fourth order Runge-Kutta numerical algorithm which was modified to fit the nacelle problem. Viscous effects on the flow field were evaluated with a viscous inviscid interacting computational model. This model was constructed by coupling the explicit Euler solution procedure with a flag entrainment boundary layer solution procedure in a global iteration scheme. The computational techniques were used to compute the flow field for a long duct turbofan engine nacelle at free stream Mach numbers of 0.80 and 0.94 and angles of attack of 0 and 4 deg.
Document ID
19850014060
Acquisition Source
Headquarters
Document Type
Thesis/Dissertation
Authors
Compton, William Bernard (George Washington Univ. Washington, DC, United States)
Date Acquired
September 5, 2013
Publication Date
May 5, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-87448
NAS 1.15:87448
N85-22371
Accession Number
85N22371
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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