Unsteady Euler algorithm with unstructured dynamic mesh for complex-aircraft aeroelastic analysisA finite-volume unstructured-grid FEM scheme with multistage Runge-Kutta time stepping is applied to the three-dimensional time-dependent Euler equations for inviscid flows on complex aircraft configurations undergoing structural deformation. The derivation of the model, the solution procedure, and the computer implementation are described, and results are presented graphically for a NASA Langley supersonic fighter aircraft model in steady and unsteady (harmonic oscillation in complete-vehicle bending mode) flow regimes. Good agreement between FEM predictions and experimental data is demonstrated.
Document ID
19890043308
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Batina, John T. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 89-1189
Meeting Information
Meeting: AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference