Aerodynamic influence coefficient computations using Euler/Navier-Stokes equations on parallel computers

An efficient procedure to compute aerodynamic influence coefficients (AICs) , using high-fidelity how equations such as Euler/Navier-Stokes equations, is presented. The AICs are computed by perturbing structures using mode sha pes. The procedure is developed on a multiple-instruction, multiple data pa rallel computer. In addition to discipline parallelization and coarse-grain parallelization of the flow domain, embarrassingly parallel implementation of ENSAERO code demonstrates linear speedup for a large number of processo rs. Demonstration of the AIC computation for static aeroelasticity analysis is made on an arrow wing-body configuration. Validation of the current pro cedure is made on a straight wing with arc airfoil at a subsonic region. Th e present flutter speed and frequency of the wing show excellent agreement with those results obtained by experiment and NASTRAN. The demonstrated lin ear scalability for multiple concurrent analyses shows that the three-level parallelism in the code is well suited for the computation of the AICs.