Shock waves interacting with turbulent boundary layers on wings can result first in self-sustained flow unsteadiness and eventually structural vibration. Due to its importance modern wing design aircraft certification, the transonic physics continue be investigated intensively. Herein we focus discussion three main aspects. First, assess a practical implementation of an iterative resolvent algo...

The mixing-plane method for calculating the three-dimensional flow through multistage turbomachinery is used to perform flutter analysis on a single stage transonic compressor. The turbomachine considered is composed of an inlet guide vane (IGV) and a compressor blade (NASA Rotor 67). The mixing-plane boundary condition enables steady and unsteady computation of the flow through multiple blade ...

Direct numerical simulations are used to investigate transonic flow acoustic resonance in an open cavity. The numerical scheme minimizes the errors due to dispersion and dissipation of acoustic waves, and resolves both the unsteady flow and radiated acoustic field. Implicit solution of the compressible Navier-Stokes equations is obtained using a compact high-order spacial differencing scheme, c...

A significant challenge to the application of evolutionary multiobjective optimization (EMO) for transonic airfoil design is the often excessive number of computational fluid dynamic (CFD) simulations required to ensure convergence. In this study, a multiobjective particle swarm optimization (MOPSO) framework is introduced, which incorporates designer preferences to provide further guidance in ...

In the present work, we propose a reformulation of the fluxes and interpolation calculations in the PISO method, a well-known pressure-correction solver. This new reformulation introduces the AUSM up flux definition as a replacement for the standard Rhie and Chow method of obtaining fluxes and central interpolation of pressure at the control volume faces. This algorithm tries to compatibilize t...