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...

A series of RANS-based aerodynamic shape optimization for an 800-passenger blended-wing-body aircraft is performed. A gradient-based optimization algorithm and a parallel structured multiblock RANS solver with Spalart–Allmaras turbulence model are used. The derivatives are computed using a discrete adjoint method considering both frozen-turbulence and full-turbulence assumptions. A total of 274...

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 ...

An adaptive method for high-order discretizations of the Reynolds-averaged NavierStokes (RANS) equations is examined. The RANS equations and Spalart-Allmaras (SA) turbulence model are discretized with a dual consistent, discontinuous Galerkin discretization. To avoid oscillations in the solution in under-resolved regions, particularly the edge of the boundary layer, artificial dissipation is ad...

This paper presents a nite element formulation for solving multidimensional compressible ows. This method is inspired by our experience with the SUPG, Finite Volume and Discontinuous-Galerkin methods. Our objective is to obtain a stable and accurate nite element formulation for multidimensional hyperbolic-parabolic problems with particular emphasis on compressible ows. In the proposed formulati...

O objetivo deste estudo foi análise numérica, via simulação realizado no ANSYS Fluent em um aerofólio de perfil NACA 4415 com variações ângulos ataque. Analisou-se a distribuição pressão e velocidade do fluido ao redor da estrutura, bem como os valores coeficientes arrasto sustentação. Por meio das equações modelo turbulência denominado Spalart-Allmaras possível encontrar as tensões turbulentas...

A computational analysis of an annular converging-diverging (CD) and an altitude adaptive expansion-deflection (ED) nozzle is presented. Numerical results were generated using a 2D axisymmetric, pressure-coupled solver in conjunction with the Spalart-Allmaras turbulence closure model and second order spatial discretisation schemes. Results were recorded over a theoretical altitude range and com...

A procedure is presented to accurately model transient motions of launch vehicles associated with complex flow conditions. The flow is modeled using the Reynolds-Averaged NavierStokes equations with the one-equation Spalart-Allmaras turbulence model. An overset grid system with a curvilinear near-body grid and a Cartesian off body is used. Solution quality is assessed using grid sensitivity and...