Transonic flutter simulations using an implicit aeroelastic solver

Flutter computations are presented for the AGARD 445.6 standard aeroelastic wing configuration using a fully implicit, aeroelastic Navier-Stokes solver coupled to a general, linear, second-order structural solver. This solution technique realizes implicit coupling between the fluids and structures using a subiteration approach. Results are presented for two Mach numbers, M∞ = 0.96 and 1.141. The computed flutter predictions are compared with experimental data and with previous Navier-Stokes computations for the same case. Predictions of the flutter point for the M∞ = 0.96 case agree well with experimental data. At the higher Mach number, M∞ = 1.141, the present computations overpredict the flutter point but are consistent with other computations for the same case. The sensitivity of computed solutions to grid resolution, the number of modes used in the structural solver, and transition location is investigated. A comparison of computations using a standard second-order accurate central-difference scheme and a third-order upwind-biased scheme is also made.

[1]  R. Gordnier.  Computation of Delta-Wing Roll Maneuvers , 1995 .

[2]  Juan J. Alonso,et al.  Multigrid unsteady Navier-Stokes calculations with aeroelastic applications , 1995 .

[3]  R. Kolonay,et al.  Unsteady aeroelastic optimization in the transonic regime , 1996 .

[4]  J. Steger,et al.  Implicit Finite-Difference Simulations of Three-Dimensional Compressible Flow , 1980 .

[5]  M. Visbal,et al.  Numerical Simulation of the Impingement of a Streamwise Vortex on a Plate , 1997 .

[6]  Charbel Farhat,et al.  Enhanced Partitioned Procedures for Solving Nonlinear Transient Aeroelastic Problems , 1998 .

[7]  P. Thomas,et al.  Geometric Conservation Law and Its Application to Flow Computations on Moving Grids , 1979 .

[8]  Miguel Visbal,et al.  Numerical simulation of spiral vortex breakdown above a delta wing , 1995 .

[9]  Miguel R. Visbal,et al.  Computation of Nonlinear Viscous Panel Flutter Using a Fully-Implicit Aeroelastic Solver , 1998 .

[10]  G. Guruswamy.  Unsteady aerodynamic and aeroelastic calculations for wings using Euler equations , 1990 .

[11]  Scott A. Morton,et al.  Fully implicit aeroelasticity on overset grid systems , 1998 .

[12]  T. Pulliam,et al.  A diagonal form of an implicit approximate-factorization algorithm , 1981 .

[13]  Miguel R. Visbal,et al.  Onset of vortex breakdown above a pitching delta wing , 1994 .

[14]  R. F. Warming,et al.  An Implicit Factored Scheme for the Compressible Navier-Stokes Equations , 1977 .

[15]  H. Lomax,et al.  Thin-layer approximation and algebraic model for separated turbulent flows , 1978 .

[16]  Miguel R. Visbal,et al.  Accuracy and Coupling Issues of Aeroelastic Navier-Stokes Solutions on Deforming Meshes , 1997 .

[17]  Lakshmi N. Sankar,et al.  Towards cost-effective aeroelastic analysis on advanced parallel computing systems , 1997 .

[18]  John T. Batina,et al.  Wing flutter computations using an aerodynamic model based on the Navier-Stokes equations , 1996 .

[19]  K. K. Gupta,et al.  Development of a finite element aeroelastic analysis capability , 1996 .

[20]  A. Jameson,et al.  Numerical solution of the Euler equations by finite volume methods using Runge Kutta time stepping schemes , 1981 .

[21]  Scott A. Morton,et al.  Implementation of a fully-implicit, aeroelastic Navier-Stokes solver , 1997 .