DNS 1-6 Description

Front Page

Description

Computational Details

Quantification of Resolution

Statistical Data

Instantaneous Data

Storage Format

Introduction

This test case features a 3:2 semi-elliptic nose with a NACA0020 tail profile mounted on a flat plate, which is representative of the wing-body junction flow problems encountered in applications of aeronautical interest. The flow features the interaction between the incipient turbulent boundary layer and the mounted airfoil and the main physical phenomenon of interest is the horseshoe vortex developping at the junction and the corner separation. This flow is also highly 3D and anisotropic regarding the turbulent stresses. Establishing a DNS database of this flow is of crucial interest since it has been shown that RANS models (both Boussinesq and Reynolds stresses-based models) display strong difficulties in recovering data from the available experiments. Such a database allows for a more thorough availability of the flow field with respect to the experiments and gives the possibility of using Machine Learning or data-assimilation techniques to improve standard RANS models.

Review of previous studies and choice of test case

A thorough listing of existing experimental and numerical studies regarding wing-body junction flows can be found in Gand et al. (2010). The present DNS is based on the configuration considered in the simulations by Apsley & Leschziner (2001), who were based themselves on the experimental studies by Devenport and Simpson (1990) and Fleming et al. (1995). The Reynolds number based on the airfoil thickness is similar to the experiment and its value is 115,000 and the flow is almost incompressible with a Mach number based on the freestream velocity of 0.078. The uDNS setup reproduces the experimental conditions but with half the experimental impacting boundary layer thickness. Therefore a direct comparison with the experimental results is not possible for the present uDNS.

Description of the test case

Geometry and flow parameters

Describe the general set up of the test case and provide a sketch of the geometry, clearly identifying location and type of boundaries. Specify the non-dimensional flow parameters which define the flow regime (e.g. Reynolds number, Rayleigh number, angle of incidence etc), including the scales on which they are based. Provide a detailed geometrical description, by preference in form of a CAD, or alternatively as lists of points and a description of the interpolation.

The following sketch displays a view of the computational domain and flow configuration geometry:

The following sketch displays the characteristic lengths of the wing:

The reference length scale is the wing chord $T$, with a corresponding Reynolds number $Re_{T}=115,000$. The computational domain size in the streamwise direction is $75T,8T$ in the spanwise direction and $3T$ in the wall-normal direction. The coordinates origin is located at the root leading edge of the airfoil. The is no flow incidence relatively to the wing, corresponding to an angle of attack of 0 degrees.

Boundary conditions

For this particular flow configuration, we aim at simulating a transitional boundary layer in order to replicate the flow conditions of the experiment. To do so, a Blasius velocity profile is imposed at the inlet corresponding to $Re_{x}=900,000$ with a uniform temperature. A laminar boundary layer is then established, and a flow perturbation is introduced at $Re_{x}=950,000$ with amplitude $A_{T}={\frac {\rho _{ref}U_{ref}^{2}}{T}}$ to trigger transition to turbulence. The total length of the boundary layer was determined such that the turbulent boundary layer thickness upwind the airfoil reaches half of the experimental value. Symmetry conditions are imposed at the lateral boundary conditions ($z=\pm 4T$). The bottom boundary is a no-slip adiabatic wall type for $xz$ planes at $y=0$ between $x=-12.75T$ and $x=17T$, and symmetry type between $x=17T$ and $x=67T$. The outlet is located away from the profile at $x=67T$, and the zone between $x=17T$ and $x=67T$ acts as a sponge layer, featuring increasingly coarse elements such that a constant flow field is recovered when reaching the outlet.

References

1. Apsley, D.D. and Leschziner, M. (2001): Investigation of Advanced Turbulence Models for the Flow in a Generic Wing-Body Junction. Flow, Turbulence and Combustion, Vol. 67, pp. 25–55
2. Gand1, F., Deck, S., Brunet, V., Sagaut, P. (2010): Flow dynamics past a simplified wing body junction. Physics of Fluids, Vol. 22, 115111 (2010)

---

Contributed by: Francesco Bassi (UNIBG), Alessandro Colombo (UNIBG), Francesco Carlo Massa (UNIBG), Michael Leschziner (ICL/ERCOFTAC), Jean-Baptiste Chapelier (ONERA) — University of Bergamo (UNIBG), ICL (Imperial College London), ONERA

Front Page

Description

Computational Details

Quantification of Resolution

Statistical Data

Instantaneous Data

Storage Format

© copyright ERCOFTAC 2024