The problem of creating high-lift propulsive aerodynamic is considered. A method was developed for constructing an profile by solving the inverse aerodynamics. dependence lifting force this on volume air sucked from its upper surface and angle attack studied. under study basis well-known Griffin/Goldschmid with suction at critical point. Three profiles have been developed. first has a flat lowe...

An incoming canonical spatially developing turbulent boundary layer (SDTBL) over a 2-D curved hill is numerically investigated via the Reynolds-averaged Navier–Stokes (RANS) equations plus two eddy-viscosity models: K−ω SST (henceforth SST) and Spalart–Allmaras SA) turbulence models. A evolving thermal has also been included, assuming temperature as passive scalar (Pr = 0.71) Prandtl number, Pr...

The study is dedicated to the peculiarities of implementing flux limiter flow quantity gradient when solving 3D aerodynamic problems using system Navier–Stokes equations on unstructured meshes. paper describes discretisation a finite-volume method and mathematical model including Spalart–Allmaras turbulence Advection Upstream Splitting Method (AUSM+) computational scheme for convective fluxes t...

The use of Active Flow Control (AFC) technologies to modify the forces acting on streamlined bodies is one most active research fields in aerodynamics. For each particular application, finding optimum set AFC parameters which maximises lift, minimises drag or lift-to-drag ratio (aerodynamic efficiency), has become a necessary design requirement. In present paper, technology was applied Selig-Do...

The turbulent flow past a wall-mounted square cylinder with an aspect ratio of 4 was investigated the aid Spalart–Allmaras improved delayed detached-eddy simulation and proper orthogonal decomposition (POD) analysis. Reynolds number equal to 12 000 (based on free-stream velocity obstacle width). boundary layer thickness ∼0.18 height. This study focused analyzing vortical structure wake vortex s...

The NASA Juncture Flow experiment is a new effort whose focus is attaining validation data in the juncture region of a wing-body configuration. The experiment is designed specifically for the purpose of CFD validation. Current turbulence models routinely employed by Reynolds-averaged Navier-Stokes CFD are inconsistent in their prediction of corner flow separation in aircraft juncture regions, s...

This chapter describes a new intelligent platform for learning optimal designs of morphing wings based on Variable Camber Continuous Trailing Edge Flaps (VCCTEF) in conjunction with a leading edge flap called the Variable Camber Krueger (VCK). The new platform consists of a Computational Fluid Dynamics (CFD) methodology coupled with a semi-supervised learning methodology. The CFD component of t...

The FInite Volume method with Exact two-phase Riemann problems (FIVER) is a robust Eulerian semi-discretization method for compressible multi-material (fluid-fluid, fluid-structure, or multi-fluid-structure) problems characterized by large density jumps and highly nonlinear structural motions and deformations. Its key components include an embedded boundary method for Computational Fluid Dynami...

An adjoint-based Navier-Stokes design and optimization method for two-dimensional multi-element high-lift configurations is derived and presented. The compressible Reynolds-Averaged Navier-Stokes (RANS) equations are used as a flow model together with the Spalart-Allmaras turbulence model to account for high Reynolds number effects. Using a viscous continuous adjoint formulation, the necessary ...