A direct numerical simulation of a supersonic turbulent boundary layer has been performed. We take advantage of a technique developed by Spalart for incompressible ow. In this technique, it is assumed that the boundary layer grows so slowly in the stream-wise direction that the turbulence can be treated as approximately homogeneous in this direction. The slow growth is accounted for by a coordi...

RANS simulations with the Spalart-Allmaras turbulence model are improved for cases flow separation using Field Inversion and Machine Learning approach. A compensatory discrepancy term is introduced into optimized high-fidelity reference data from experiments. Influences on optimization results respect to regularization, grid resolution areas in which active investigated. Finally, a neural netwo...

The work presented in this article aims to the calculation of the aerodynamic characteristics of the NREL phase II rotor that is a horizontal axis downwind wind turbine rotor and which is assumed to stand isolated in the space. The Reynolds averaged Navier-Stokes equations combined with the Spalart-Allmaras turbulence model that describes the three dimensional steady state flow about the wind t...

An acoustic prediction capability for supersonic axisymmetric jets was developed on the basis of OVERFLOW Navier-Stokes CFD (Computational Fluid Dynamics) code of NASA Langley Research Center. Reynolds-averaged turbulent stresses in the flow fie ld are modeled with the aid of Spalart-Alimaras one-equation turbulence modeL Appropriate acoustic and outflow boundary conditions were implemented to ...

A time discretization scheme based on the third-order backward difference formula has been embedded into a Chebyshev tau spectral method for the Navier-Stokes equations. The time discretization is a variant of the second-order backward scheme proposed by Krasnov et al. (J. Fluid Mech., 2008). Highresolution direct numerical simulations of turbulent incompressible channel flow have been performe...

The adjoint approach in gradient-based optimization combined with computational fluid dynamics is commonly applied in various engineering fields. In this work, the gradients are used for the design of a two-dimensional airfoil shape, where the aim is a change in lift and drag coefficient, respectively, to a given target value. The optimizations use the unconstrained quasi-Newton method with an ...