Advanced flow simulation methods in aircraft design

Abstract

The compressible Navier‐Stokes equations are solved numerically for turbulent transonic aerospace applications on parallel computers. An Explicit Algebraic Reynolds Stress Model (EARSM) models the turbulence. Expressing the EARSM as an extension of an eddy‐viscosity model makes the implementation straightforward in a flow solver with existing two‐equation eddy‐viscosity models. The k−ω transport equations are used as a platform for the model. The EARSM approach significantly improves the shock position for transonic flow over wings without substantial increase in computational cost. Industrial use of advanced flow modelling requires a short turn‐around time of computations. This is enabled through the use of parallel computers. To achieve good parallel performance the computational load has to be evenly distributed between the processors of the parallel computer. A heuristic algorithm is described for distributing and splitting the blocks of a structured multiblock grid for a good static load balance. Speed‐up results are presented for turbulent flow around a wing on a number of parallel platforms.

Citation

Sillén, M. (2002), "Advanced flow simulation methods in aircraft design", Aircraft Engineering and Aerospace Technology, Vol. 74 No. 2, pp. 138-146. https://doi.org/10.1108/00022660210420843