Aeroelastic calculations for the hawk aircraft using the euler equations

This paper demonstrates coupled time-domain computational-fluid-dynamics (CFD) and computationalstructural-dynamics simulations for flutter analysis of a real aircraft in the transonic regime. It is shown that a major consideration for a certain class of structural models is the transformation method, which is used to pass information between the fluid and structural grids. The aircraft used for the calculations is the BAE Systems Hawk. A structural model, which has been developed by BAE Systems for simplified linear flutter calculations, only has a requirement for O(10) degrees of freedom. There is a significant mismatch between this and the surface grid on which loads and deflections are defined in the CFD calculation. This paper extends the constant volume tetrahedron tranformation, previously demonstrated for wing-only aeroelastic calculations, to multicomponent, or full aircraft, cases and demonstrates this for the Hawk. A comparison is made with the predictions of a linear flutter code.

[1]  Carlos E. S. Cesnik,et al.  Evaluation of computational algorithms suitable for fluid-structure interactions , 2000 .

[2]  Reid Melville.  Nonlinear simulation of F-16 aeroelastic instability , 2001 .

[3]  Gregory W. Brown,et al.  Application of a three-field nonlinear fluid–structure formulation to the prediction of the aeroelastic parameters of an F-16 fighter , 2003 .

[4]  B. V. Leer,et al.  Towards the ultimate conservative difference scheme. II. Monotonicity and conservation combined in a second-order scheme , 1974 .

[5]  C. Farhat,et al.  Two efficient staggered algorithms for the serial and parallel solution of three-dimensional nonlinear transient aeroelastic problems , 2000 .

[6]  Ken Badcock,et al.  Intergrid Transformation for Aircraft Aeroelastic Simulations , 2004 .

[7]  Charbel Farhat,et al.  Geometric conservation laws for flow problems with moving boundaries and deformable meshes, and their impact on aeroelastic computations , 1996 .

[8]  W. J. Gordon,et al.  Construction of curvilinear co-ordinate systems and applications to mesh generation , 1973 .

[9]  Germaine Stanislasse Laure Goura.  Time marching analysis of flutter using computational fluid dynamics , 2001 .

[10]  David J. Lucia,et al.  Aeroelastic System Development Using Proper Orthogonal Decomposition and Volterra Theory , 2003 .

[11]  H. Tsai,et al.  Unsteady Flow Calculations with a Parallel Multiblock Moving Mesh Algorithm , 2001 .

[12]  Stanley Osher,et al.  Upwind schemes and boundary conditions with applications to Euler equations in general geometries , 1983 .

[13]  Russ D. Rausch,et al.  Three-dimensional time-marching aeroelastic analyses using an unstructured-grid Euler method , 1992 .

[14]  B. Richards,et al.  Elements of computational fluid dynamics on block structured grids using implicit solvers , 2000 .

[15]  Ken Badcock,et al.  Aeroelastic Damping Model Derived from Discrete Euler Equations , 2006 .

[16]  K. Badcock,et al.  Fast prediction of transonic aeroelastic stability and limit cycles , 2007 .

[17]  S. P. Spekreijse,et al.  Simulation of limit cycle oscillation of fighter aircraft at moderate angle of attack , 2003 .

[18]  S. Brown,et al.  Displacement extrapolations for CFD+CSM aeroelastic analysis , 1997 .

[19]  Ken Badcock,et al.  Extrapolation effects on coupled computational fluid dynamics/computational structural dynamics simulations , 2003 .

[20]  Ken Badcock,et al.  A Reduced Order Model for Damping Derived from CFD Based Aeroelastic Simulations , 2006 .

[21]  Bryan E. Richards,et al.  A data exchange method for fluid-structure interaction problems , 2001 .

[22]  A. Jameson.  Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings , 1991 .

[23]  R. Britt,et al.  Simulation of Non-Linear Transonic Aeroelastic Behavior on the B-2 , 1999 .

[24]  Ken Badcock,et al.  Implicit method for the time marching analysis of flutter , 2001 .