The increased traffic emissions and reduced ventilation of urban street canyons lead to the formation of high particle concentrations as a function of the related flow field and geometry. In this context, the use of advanced modelling tools, able to evaluate particle concentration under different traffic and meteorological conditions, may be helpful. In this work, a numerical scheme based on th...

Unlike in the case of high Reynolds number airfoil, selecting a turbulent closure model for low airfoil is still challenge. A used not necessarily suitable due to presence separation bubbles airfoil. In this study, we two simple models, Spalart-Allmaras and k- , calculating thrust coefficient as propeller determine their accuracy. It was found that there significant discrepancy between numerica...

Numerical simulations are performed using a Reynolds-averaged Navier-Stokes (RANS) flow solver for a circulation control airfoil. 2D and 3D simulation results are compared to a circulation control wind tunnel test conducted at the NASA Langley Basic Aerodynamics Research Tunnel (BART). The RANS simulations are compared to a low blowing case with a jet momentum coefficient, Cμ, of 0.047 and a hi...

Reynolds averaged Navier-Stokes methods often cannot predict shock/turbulence interaction correctly. This may be because RANS models do not account for the unsteady motion of the shock wave that is inherent in these interactions. Sinha et al. [Phys. Fluids, Vol. 15, No. 8 (2003)] propose a shock-unsteadiness correction that significantly improves turbulence prediction across a normal shock in a...

We evaluate the applicability of a production computational fluid dynamics code for conducting detached eddy simulation for unsteady flows. A second-order accurate Navier-Stokes code developed at NASA Langley Research Center, known as TLNS3D, is used for these simulations. We focus our attention on high Reynolds number flow (Re = 5× 10 − 1.4× 10) past a circular cylinder to simulate flows with ...

The aerodynamic analysis of wind turbine rotors using preconditioned weighted essentially non-oscillatory scheme to solve the compressible NavierStokes equations in non-inertial coordinate system with Spalart-Allmaras one equation turbulence model is presented. A parallel clustering algorithm based on Message Passing Interface library was implemented. The NREL Phase VI rotor with S809 airfoil w...

In this paper, the continuous adjointmethod to compute shape sensitivities in aerodynamic designwith turbulence modeling is described and developed. The focus is on compressible flows described by the Reynolds-averaged Navier–Stokes equations and the classical Spalart–Allmaras model for turbulence. Turbulence modeling usually requires, in particular, computation of the distance to the surface. ...

This paper presents several test cases that were used to validate the implementation of two turbulence models in UNS3D code, an in-house code. The Shear Stress Transport model and Spalart–Allmaras model. These explored using numerical results generated by three computational fluid dynamics codes: NASA’s FUN3D CFL3D, UNS3D. Four considered: a flat plate case, airfoil near-wake, backward-facing s...