To study the free rolling movement of a 65? swept sharp leading edge delta wing with aileron deflection, unsteady Euler/Navier-Stokes equations are solved synchronously with the free rolling motion equation of a rigid body. Navier-Stokes simulations are conducted adopting the detached-eddy simulation (DES) based on an Spalart-Allmaras model. In the context of a multiblock structured grid, the arc-length based transfinite interpolation (TFI) method is employed to realize the aileron deflection, while the rolling of the wing is achieved by rotating the whole grid. The analysis of the responses of free-to-roll movement due to the scheduled aileron deflections shows that this delta wing has three different equilibrium positions during rolling which couple well between the two approaches. The wing at the three equilibrium locations are (1) due to symmetric flow, (2) characterized by vortex breakdown on the portside and separated vortex on the starboard side of the wing and dominated by their vortex strength difference, (3) resulting from the rolling moment balance between the contributions from the aileron deflection and leading edge vortices. Additionally, the rolling motion of the delta wing is very sensitive to the amplitude of the aileron deflection angle, which influences the final equilibrium position and the path to it.
LI Xile
,
YANG Yong
. Numerical Simulation of the Free Rolling Motion of a Delta Wing Configuration with Aileron Deflection[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012
, (3)
: 453
-462
.
DOI: CNKI:11-1929/V.20111125.1301.001
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