In this paper, we present recent improvements of an Immersed Boundary Method (IBM) for the simulation turbulent compressible flows on Cartesian grids. The proposed approach enables to remove spurious oscillations at wall skin pressure and friction coefficients. Results are compared a body-fitted using same function, showing that stair-step immersed boundary provides smooth solution one. method ...

Abstract To further develop a more effective turbulence model and improve the calculation accuracy of flow, new was constructed using deformation rate tensor, grouping average. Due to need evaluate applicability in numerical calculation, flow around NACA0012 airfoil with Mach number 0.15 multiple angles attack calculated on OpenFOAM platform based grid independence research. The Spalart-Allmara...

This paper presents a novel level-set-based approach to model evolving boundary problems for in-flight ice accretion. No partial differential equations are solved as in the standard level-set formulation, but simple geometrical quantities employed provide an implicit discretization of updated boundary. method avoids mesh entanglements and grid intersections typical algebraic deforming technique...

The efficiency of an airfoil can be improved by adjusting its surface. CFD software was used to investigate a 2D with and without spanwise semicircular groove on the upper NACA0012 airfoils grooves were analyzed using k-ω turbulence model. lift drag coefficients compared. To effect location efficiency, added in various locations compared smooth airfoil. flow velocity remained constant at 20 m/s...

The discontinuous Galerkin domain decomposition (DGDD) method couples subdomains of high-fidelity polynomial approximation to regions low-dimensional resolution for the numerical solution systems conservation laws. In low-fidelity regions, is approximated by empirical modes constructed Proper Orthogonal Decomposition and a reduced-order model used predict solution. high-dimensional instead solv...

Flexible flapping wings have garnered a large amount of attention within the micro aerial vehicle (MAV) community: a critical component of MAV flight is the coupling of aerodynamics and structural dynamics. This paper presents a computational framework for simulating shell-like wing structures flapping in incompressible flow at low Reynolds numbers in both hover and forward flight. The framewor...

The development of a multi-model formulation to simulate three dimensional compressible flows on parallel computers is presented. The goal is to reduce the overall time and memory required to simulate the flow by using locally selected cheaper and more computational efficient physical models without sacrificing the global fidelity of the simulation. Our approach involves splitting the computati...

The article deals with an improved treatment of wall models for the simulation turbulent flows in framework Immersed Wall Boundaries on Cartesian grids. emphasis is put implementation a Lattice-Boltzmann Method solver without loss generality, since proposed approach can be used Navier–Stokes-based solvers straightforward way. model relies combination several key elements, namely i) removal grid...

10 In this work we extend the high-order Discontinuous Galerkin (DG) Finite element 11 method to inviscid low Mach number flows. The method here presented is designed 12 to improve the accuracy and efficiency of the solution at low Mach numbers using 13 both explicit and implicit schemes for the temporal discretization of the compress14 ible Euler equations. The algorithm is based on a classica...

A concept of ”static reconstruction” and ”dynamic reconstruction” was introduced for higher-order (third-order or more) numerical methods in our previous work. Based on this concept, a class of hybrid DG/FV methods had been developed for one-dimensional conservation law using a ”hybrid reconstruction” approach, and extended to two-dimensional scalar equations on triangular and Cartesian/triangu...