عنوان مقاله [English]
Determining aerodynamic coefficients and control and stability derivatives play an
important role in the development of flight vehicles. In this paper, roll damping coefficient
of BASIC FINNER standard model is determined at different attack angles and with
various Mach numbers using numerical Sliding Mesh method. Also, the impact of the
effective parameters such as amplitude and frequency of oscillation, time step and number
of iteration in each step in numerical solution are investigated to determine the roll
damping coefficients. Geometry modeling and grid generation and the flow analysis are
done by ANSYS CFX and ANSYS FLUENT software, respectively. In this simulation,
Euler’s flow equations, compressible and unsteady flow, finite volume method and density
based solver with explicit formulation and first-order accuracy for a numerical solution
are used. To evaluate the results of a numerical study, a comparison is made between the
experimental data and MD results, indicating that the results have a good accuracy.
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