To improve the calculation of the flow properties of an aerospike nozzle, different turbulence models were investigated in this study. The primary shape of the nozzle plug is determined through utilizing an approximate method. The flow field is, then, simulated using the Navier-Stokes equations for compressible flows. The commercial computational fluid dynamics code Fluent is used to simulate t...

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...

Three Reynolds-Stress Models (RSMs) have been benchmarked on industrial configurations with aeronautical applications. The models are first compared a zero-pressure-gradient boundary layer, which highlights the differences in near-wall approaches of models. Results then analyzed for Skåre & Krogstad adverse-pressure-gradient layer and Common Research Model (CRM) aircraft two Reynolds numbers. B...

The paper presents computational prediction of aerodynamic hysteresis loops in static conditions for a two-dimensional aerofoil that was used as cross-section profile rectangular wing with an aspect ratio five, tested the TsAGI T-106 wind tunnel at Reynolds number and Mach . Tests showed minor changes curvature leading edge thin lead to significant increase maximum lift coefficient when appear ...

A significant extension of previously introduced continuous eddy simulation methods is presented by introducing minimal error partially and fully resolving for turbulent flows. This approach represents a machine learning strategy the hybridization modeling-focused resolution-focused methods. It can be applied to well-known equation structures (Spalart–Allmaras type equations, usually two-equati...

The work in this paper aims to increase the maximum lift coefficient of airfoil by implementing co-flow jet concept on NACA 0018 and also investigate performance (CFJ) airfoil. To conduct numerical solution, RANS equations have been solved for 2D incompressible unsteady flow using Spalart-Allmaras turbulence model. suction surface is modified placing injection slot near leading edge trailing ed...

The paper presents the results of simulation unsteady turbulent flow generated by helicopter main rotor in presence fuselage with an emphasis on analysis influence rotor-induced and rotor-generated acoustic field. Reynolds-averaged Navier–Stokes equations Spalart–Allmaras turbulence model are used to simulate Caradonna–Tung ROBIN interaction hovering flight. governing discretized using vertex-c...

In this paper, a turbulence model based on deep neural network is developed for turbulent flow around airfoil at high Reynolds numbers. According to the data got from Spalart-Allmaras (SA) model, we build that maps features eddy viscosity. The then used replace SA mutually couple with CFD solver. We suitable data-driven mainly inputs, outputs and loss function of model. A feature selection meth...