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...

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...

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 design of the thermal protection system requires high-precision and high-reliability CFD simulation for validation. To accurately predict hypersonic aerodynamic heating, an overall strategy based on mutual selection is proposed. Foremost, grid criterion wall cell Reynolds number developed. Subsequently, dependence turbulence model discretization scheme considered. It suggested that appropri...

In this paper, two-dimensional computational fluid dynamics analyses were conducted to examine the rib effect on performance of NACA 0018 plain flapped airfoil. A mesh independence study was carried out and Spalart-Allmaras turbulence model selected for validation. Four various airfoil models designed: M1 (airfoil without flap structure), M2 with M3 a flap) M4 structure flap). The designed airf...