Aeroservoelastic simulation of realistic configurations requires the representation of moving control surfaces. Once a control surface is deflected, for example, at the trailing edge of a wing, the surface is no longer continuous and this is considered here. A sliding grid approach is used to allow control surface deflection within a multiblock-structured grid framework. Two methods of information transfer between patched (non-matching) grids are developed and tested in this paper: the first involving halo interpolation and the second, conservative flux interpolation. Results are presented for a range of test cases involving steady and unsteady flows using non-matching and sliding interfaces at block boundaries. It is shown that both methods can be applied to the example of a wing with a deflected control surface, where no advantage is gained by using a significantly more complex, conservative method.
KousenK. A.BendiksenO. O.Non-linear aspects of the transonic aeroelastic stability problem. AIAA Paper No. 88–2306. Also in AIAA/ASME/ASCE/AHS 29th Structures, Structural Dynamics and Material Conference, 1988.
2.
KousenK. A.BendiksenO. O.Limit cycle phenomena in computational transonic aeroelasticity. J. Aircraft, 1994, 31 (6), 1257–1263.
3.
AlonsoJ. J.JamesonA.Fully-implicit timemarching aeroelastic solutions, AIAA Paper No. 94–0056, January 1994.
4.
GuruswamyG. P.Unsteady aerodynamic and aeroelastic calculations for wings using Euler equations. AIAA J., 1990, 28 (3), 461–469.
5.
RobinsonB. A.BatinaJ. T.YangH. T. Y.Aeroelastic analysis of wings using the Euler equations with a deforming mesh. J. Aircraft, 1991, 28 (11), 781–788.
6.
MeijerJ. J.HounjetM. H. L.EussenB. J.G.PranantaB. B.Nlr-tu delf experience in unsteady aerodynamics and aeroelastic simulation applications. Technical Report No. 822, AGARD, March 1998, Numerical Unsteady Aerodynamic and Aeroelastic Simulation, pp. 11–1–11–21.
7.
SchulzeS.Transonic aeroelastic simulation of a flexible wing section. Technical Report No. 822, AGARD, March 1998. Numerical Unsteady Aerodynamic and Aeroelastic Simulation, pp. 10–1–11–20.
8.
GouraG. S. L.BadcockK. J.WoodgateM. A.RichardsB. E.Implicit method for the time marching analysis of flutter. Aeronaut. J., 2001, 105 (4), 199–214.
9.
BendiksenO. O.KousenK. A.Transonic flutter analysis using the Euler equations. AIAA Paper No. 87–0911-CP, 1987.
10.
BatinaJ. T.YoungT. Y.Application of transonic codes to aeroelastic modelling of airfoils including active controls. J. Aircraft, 1984, 21 (8), 623–630.
11.
Lee-RauschE.M.BatinaJ. T.Wing flutter boundary prediction using unsteady Euler aerodynamic method. J. Aircraft, 1985, 32 (2), 416–422.
12.
StephensC. H.ArenaA. S.JrGuptaK. K.CFD-based aeroservoelastic predictions with comparisons to benchmark experimental data. AIAA Paper No 99–0766, 1999.
13.
SedaghatA.CooperJ. E.WrightJ. R.LeungA. Y. T.Curve fitting approach for transonic flutter predicitons. Aeronaut. J., 2003, 107 (1075), 565–572.
14.
KandilO. A.MasseyS. J.ShetaE. F.Structural dynamics-CFD interaction for computation of vertical tail buffet. Aeronaut. J., 1996, 100, 297–303.
TaylorN. V.AllenC. B.FenwickC. L.DjayapertapaL.Investigation of flutter suppression by active control. In 21st AIAA Applied Aerodynamics Conference, Florida, AIAA Paper No. 2003–3510, 2003.
17.
DjayapertapaL.AllenC. B.FiddesS. P.Two-dimensional transonic aeroservoelastic computations in the time domain. Int. J. Numer. Methods Eng., 2001, 52 (12), 1355–1377.
18.
AllenC. B.TaylorN. V.FenwickC. L.GaitondeA. L.JonesD. P.A comparison of full nonlinear, and reduced order aerodynamic models in control law design for active flutter suppression. Int. J. Numer. Methods Eng., 2005, 64 (12), 1628:1648.
JonesD. P.GaitondeA. L.FiddesS. P.Moving mesh generation for unsteady flows about deforming complex geometries. CFD J. Japanese Soc. CFD, 2001, 430–439, Special Issue.
21.
JonesD. P.Force transfer in aeroelastic calculations, Technical Report Department of Aerospace Engineering Report AE046 University of Bristol, 2002.
TaylorN. V.AllenC. B.GaitondeA. L.JonesD. P.HillG. F. J.Investigation of structural modelling methods for aeroelastic calculations In Proceedings AIAA 22nd Applied Aerodynamics Conference, Rhode Island, August 2004, Paper 5370.
24.
FenwickC. L.Consideration of control surfaces in time-domain aeroelastic simulations, Technical Report Department of Aerospace Engineering Report AE045 University of Bristol, 2003.
25.
TangH. S.ZhouT.On nonconservative algorithms for grid interfaces. SIAM J. Numer. Anal., 1999, 37 (1), 173–193.
26.
BergerM. J.On conservation at grid interfaces. SIAM J. Numer. Anal., 1987, 24 (5), 967–984.
27.
RaiM. M.A relaxation approach to patched-grid calculations with the Euler equations. Technical Report 85–0295, AIAA, 1985.
28.
RaiM. M.A conservative treatment of zonal boundaries for Euler equation calculations. J. Comput. Phys., 1986, 62 (2), 472–503.
29.
LeratA.WuZ. N.Stable conservative multidomain treatments for implicit Euler solvers. J. Comput. Phys., 1996, 123, 45–64.
30.
BohbotJ.GrondinG.CorjonA.DarracqD.A parallel multigrid conservative patched/sliding mesh algorithm for turbulent flow computation of 3D complex aircraft configurations. Technical Report 2001–1006, AIAA, 2001.
31.
Van-LeerB.Flux-vector splitting for the Euler equations. Lecture Notes Phys., 1982, 170, 507–512.
AndersonW. K.ThomasJ. L.Van-LeerB.Comparison of finite volume flux vector splittings for the Euler equations. AIAA J., 1986, 24, 1453–1460.
34.
JamesonA.Time dependent calculations using multigrid with applications to unsteady flows past airfoils, and wings. Technical Report 91–1596, AIAA, 1991.
35.
AllenC. B.Multigrid convergence of inviscid fixed-, and rotary-wing flows. Int. J. Numer. Methods Fluids, 2002, 39 (2), 121–140.
36.
AllenC. B.An unsteady multiblock multigrid scheme for lifting forward flight simulation. Int. J. Numer. Methods Fluids, 2004, 45 (9), 973–984.
37.
ScottR. C.HoadleyS. T.WiesemanC. D.DurhamM. H.The benchmark active controls technology model aerodynamic data. Technical Report 97–0829, AIAA, 1997.
38.
WaszakM. R.Modelling the benchmark active control technology wind-tunnel model for application to flutter suppression. Technical Report 96–3437, AIAA, 1996.
