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...

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...

Field inversion and machine learning are implemented in this study to describe three-dimensional (3D) separation flow around an axisymmetric hill augment the Spalart–Allmaras (SA) model. The discrete adjoint method is used solve field problem, artificial neural network as A validation process for proposed adjust hyperparameters obtain a physically acceptable solution. result shows that non-equi...

Accurate simulation of turbulent flow with separation is an important but challenging problem. In this paper, a data-driven Reynolds-averaged turbulence modeling approach, field inversion and machine learning implemented to modify the Spalart–Allmaras model separately on three cases, namely, S809 airfoil, periodic hill GLC305 airfoil ice shape 944. Field based discrete adjoint method used quant...

Numerical simulations of the flow surrounding particle agglomerates were carried out using computational fluid dynamics to assess ability five RANS turbulence models estimate drag coefficient in agglomerates. Simulations steady conditions for Reynolds numbers between 1 and 1500. Streamlines showed that symmetrical present a velocity profile similar single sphere profile. Results both Spalart-Al...

This paper presents an original approach regarding the application of sweep to rotating blade cascades. The justification for swept blades is given by its consequence, i.e. a reduction of local velocity (usually from supersonic/ transonic to subsonic regimes) such that the losses due to shock waves and/or boundary layer displacement and/or followed by reattachment are minimized. As study cases ...

Manoeuvring underwater vehicles experience complex three dimensional flow. Features include stagnation and boundary layer separation along a convex surface. The resulting free vortex sheet rolls up to form a pair of streamwise body vortices. The track and strength of the body vortex pair results in a nonlinear increase in lift with as body incidence increases. Consequently, accurate capture of ...