Wing-Body Aeroelasticity Using Finite-Difference Fluid/Finite-Element Structural Equations on Parallel Computers

In recent years significant advances have been made for parallel computers in both hardware and software. Now parallel computers have become viable tools in computational mechanics. Many application codes developed on conventional computers have been modified to benefit from parallel computers. Significant speedups in some areas have been achieved by parallel computations. For single-discipline use of both fluid dynamics and structural dynamics, computations have been made on wing-body configurations using parallel computers. However, only a limited amount of work has been completed in combining these two disciplines for multidisciplinary applications. The prime reason is the increased level of complication associated with a multidisciplinary approach. In this work, procedures to compute aeroelasticity on parallel computers using direct coupling of fluid and structural equations will be investigated for wing-body configurations. The parallel computer selected for computations is an Intel iPSC/860 computer which is a distributed-memory, multiple-instruction, multiple data (MIMD) computer with 128 processors. In this study, the computational efficiency issues of parallel integration of both fluid and structural equations will be investigated in detail. The fluid and structural domains will be modeled using finite-difference and finite-element approaches, respectively. Results from the parallel computer will be compared with those from the conventional computers using a single processor. This study will provide an efficient computational tool for the aeroelastic analysis of wing-body structures on MIMD type parallel computers.

[1]  K. Law.  A parallel finite element solution method , 1986 .

[2]  V. Murti,et al.  Numerical inverse isoparametric mapping in remeshing and nodal quantity contouring , 1986 .

[3]  K. Gramoll,et al.  STRUCTURAL ANALYSIS OF A FLEXIBLE STRUCTURAL MEMBER PROTRUDING INTO AN INTERIOR FLOW FIELD , 1993 .

[4]  Guru P. Guruswamy,et al.  Coupled finite-difference/finite-element approach for wing-body aeroelasticity , 1992 .

[5]  T. Yang,et al.  Aeroelastic time response analysis of thin airfoils by transonic code LTRAN2 , 1981 .

[6]  K. Appa,et al.  The determination of load and slope transformation matrices for aeroelastic analysis , 1985 .

[7]  Guru P. Guruswamy,et al.  Fluid-structural interactions using Navier-Stokes flow equations coupled with shell finite element structures , 1993 .

[8]  Guru P. Guruswamy,et al.  Ensaero—A multidisciplinary program for fluid/structural interaction studies of aerospace vehicles , 1990 .

[9]  Nathan M. Newmark,et al.  A Method of Computation for Structural Dynamics , 1959 .

[10]  Raymond Ching-Chung Luh,et al.  Interactive surface grid generation , 1991 .

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

[12]  R. F. Warming,et al.  An implicit finite-difference algorithm for hyperbolic systems in conservation-law form. [application to Eulerian gasdynamic equations , 1976 .

[13]  Kari Appa,et al.  Finite-surface spline , 1989 .

[14]  Guru P. Guruswamy,et al.  Vortical flow computations on a flexible blended wing-body configuration , 1991 .

[15]  R. N. Desmarais,et al.  Interpolation using surface splines. , 1972 .

[16]  Sisira Weeratunga,et al.  Parallel computation of 3-D Navier-Stokes flowfields for supersonic vehicles , 1993 .

[17]  R. Pidaparti,et al.  Structural and aerodynamic data transformation using inverse isoparametric mapping , 1992 .