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Navier-Stokes simulation of external/internal transonic flow on the forebody/inlet of the AV-8B Harrier IIIn this work, the computation of combined external/internal transonic flow on the complex forebody/inlet configuration of the AV-8B Harrier II is performed. The actual aircraft has been measured and its surface and surrounding domain, in which the fuselage and inlet have a common wall, have been described using structured grids. The 'thin-layer' Navier-Stokes equations were used to model the flow along with the Chimera embedded multi-block technique. A fully conservative, alternating direction implicit (ADI), approximately factored, partially fluxsplit algorithm was employed to perform the computation. Comparisons to some experimental wind tunnel data yielded good agreement for flow at zero incidence and angle of attack. The aim of this paper is to provide a methodology or computational tool for the numerical solution of complex external/internal flows.
Document ID
19930064237
Document Type
Conference Paper
Authors
Mysko, Stephen J. (NASA Ames Research Center Moffett Field, CA, United States)
Chyu, Wei J. (NASA Ames Research Center Moffett Field, CA, United States)
Stortz, Michael W. (NASA Ames Research Center Moffett Field, CA, United States)
Chow, Chuen-Yen (Colorado Univ. Boulder, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 93-3057
Meeting Information
AIAA, Fluid Dynamics Conference(Orlando, FL)
Distribution Limits
Public
Copyright
Other