Aerodynamic Influence Coefficient Computations Using Euler/Navier-Stokes Equations on Parallel Computers

An efficient procedure to compute aerodynamic influence coefficients (AIC) using high fidelity flow equations such as Euler/Navier- Stokes equations is presented. The AIC's are computed by perturbing structures using mode shapes. The procedure is developed on a multiple-instruction, multiple-data (MIMD) parallel computer. In addition to discipline parallelization and coarse-grain parallelization of the flow domain, embarrassingly parallel implementation of ENS AERO code demonstrates linear speedup for a large number of processors. Demonstration of the AIC computation for static aeroelasticity analysis is made on an arrow wing-body configuration. The computations show that some of the AIC's do not converge at the lower perturbation range since the perturbation is too small to prevail over the initial aerodynamic loads. The effect of initial aerodynamic loads disappears with increasing perturbation amplitude. The demonstrated linear scalability for multiple concurrent analyses shows that the threelevel parallelism in the code is well suited for the computation of the AIC's.