Aeroelastic Computations on Wing-Body-Control Configurations on Parallel Computers

Abstract

A multizonal capability for aeroelastic computation of complex geometries has been implemented in ENSAERO, an aeroelastic analysis code with Euler/Navier ‐ Stokes e ow solver, on the IBM SP2 parallel computer. The discipline parallelization is achieved by distributing the e uid, structure, and control domains onto different groups of computational nodes. The e uid domain is further parallelized based on the multizonal method. The coupling between the e uids and structures is obtained by exchanging the interface boundary data at every iteration by using the explicit message passing interface standard library. The performance of the current implementation shows that about 12 computational nodes of the SP2 computer are equivalent to the speed of a single C90 processor. For demonstration purposes, static aeroelastic computations coupled with control surfaces are made for an arrow wing ‐ body ‐ control cone guration in the transonic e ow regime. Computed pressure coefe cients for a rigid cone guration were compared with the wind-tunnel experiment. The two results show good agreement. Steady aeroelastic simulations are made with and without control surface dee ections. The static aeroelastic simulations show that the effect of e exibility is signie cant on aerodynamic coefe cients. It is noted that the e exible wing lowered the sectional lifts compared to the rigid wing. This procedure can be utilized for the fast computational solution of large-scale wind-tunnel models and real cone gurations that inevitably deform under aerodynamic loads.