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Simulation of tail buffet using delta wing-vertical tail configurationComputational simulation of the vertical tail buffet problem is accomplished using a delta wing-vertical tail configuration. Flow conditions are selected such that the wing primary-vortex cores experience vortex breakdown and the resulting flow interacts with the vertical tail. This multidisciplinary problem is solved successively using three sets of equations for the fluid flow, aeroelastic deflections and grid displacements. For the fluid dynamics part, the unsteady, compressible, full Navier-Stokes equations are solved accurately in time using an implicit, upwind, flux-difference splitting, finite-volume scheme. For the aeroelastic part, the aeroelastic equation for bending vibrations is solved accurately in time using the Galerkin method and the four-stage Runge-Kutta scheme. The grid for the fluid dynamics computations is updated every few time steps using a third set of interpolation equations. The computational application includes a delta wing of aspect ratio 1 and a rectangular vertical tail of aspect ratio 2, which is placed at 0.5 root-chord length downstream of the wing trailing edge. The wing angle of attack is 35 deg and the flow Mach number and Reynolds number are 0.4 and 10,000, respectively.
Document ID
19930064360
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kandil, Osama A.
(NASA Langley Research Center Hampton, VA, United States)
Kandil, Hamdy A.
(NASA Langley Research Center Hampton, VA, United States)
Massey, Steven J.
(Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-3688
Accession Number
93A48357
Funding Number(s)
CONTRACT_GRANT: NAG1-648
Distribution Limits
Public
Copyright
Other

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