Simulation of wing-body junction flows with hybrid RANS/LES methods

Introduction

Junction flow occurs when a boundary layer encounters an obstruction
At realistic

Viewed objects

Rood wing-body junction (3:2 elliptical nose and a NACA 0020

Numerical methods. Flow equations

The computations here are all based on a

Numerical methods. Energy and dissipation equations

Using the LU-SGS method
The production terms

Results. Rood

Boundary conditions:
at x/T = -18.24: inlet (from experiment)
at x/T

Difference between SST and WD+

Comparisons on U and k with the

Difference on grid

Comparisons on U/Uref and k/U2ref based on two grids

Flowfields on the symmetric plane

Comparison of velocity vectors on the symmetric

Flow structures at three streamwise positions

Transverse velocity at different streamwise positions

Flow structures at three streamwise positions

Flow patterns around the wing-body junction

Flow structures at three streamwise positions

Comparisons of turbulent kinetic energy and

Flowfields in the wake

Comparisons of turbulent kinetic energy and the vertical

Results. TN D-712 junction

Grids around TN D-712 Wing-fuselage junction.

Mach number - 0.9
Reynolds number is 7.5 · 106 (based on

Pressure coefficients

Comparisons of pressure coefficients of different turbulence methods near the

Vortex over the wing

Comparison on vortex over the wing with RANS,

The instantaneous DDES vorticities over the wing at different AoAs (Left:

Flow patterns of DDES

Transverse flow structure at different streamwise positions by