22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.7.R1
NUMERICAL STRUCTURAL ANALYSIS OF VISCOUS COMPRESSIBLE FLOW PAST AN AIRFOIL AND BODY OF REVOLUTION
Z. Dzygadlo, S. Wrzesien
Military University of Technology, Poland
Keywords: viscous compressible flow, airfoil and body of revolution, numerical structural
analysis
Application of modern methods of computer
analysis enable us to solve problems of viscous
compressible flows making use of the Navier-
Stokes equations.
The problems to be studied in the present
paper are those of a sharp edged airfoil and a
body of revolution flown-past by viscous, heat
conducting gas, the complete Navier-Stokes
equations being used. The case of a boundary
layer and an oblique shock wave formed
simultaneously in the same region of the flow
will be considered, thus enabling us to
determine the influence of dissipative properties
of the gas on course of those phenomena.
The problem has been solved by the
method of decomposition of the set of equations
and fractional steps as well as an iterative
procedure with respect to time. This set of
equations was approximated by an implicit
double-layer difference scheme of the Cranck-
Nicholson type.
The method of decomposition, which was
used, enabled us to devise the method of
numerical analysis, based on an implicit
difference scheme in the form of an algorithm
with alternating directions and separation of
physical processes.
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