Parallel computing has been a trend in the aerospace industry already for more than a decade. At the Division of Fluid Mechanics at LTH, a flow-solver for numerical aeronautical simulations was developed, which proved to have very good parallel performance. The code uses PVM and is intended to run on both heterogeneous and homogeneous distributed memory architectures. It is written in the C language and has a modular structure which permits one to plug-in independent modules, such as the spray module for instance. A brief description of the numerical algorithm is given, additional information can be found in. this chapter mainly reports on the parallel algorithm employed in the code. The code employs an efficient algorithm, based on the Residual Distribution Scheme approach, well suited for parallelization. The ParNAS3D solver has been coupled with an independent spray-module for LES of spray in compressible flows. The combined LES-spray code has been used to investigate the injection, mixing and evaporation processes of a fuel spray in a gas turbine engine. This chapter also presents the numerical algorithm employed in the code.
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