# Numerical investigation of the flow field around $$65^\circ$$ delta wing using the unstructured code zCFD¶

Authors: A. Cimpoeru (CFMS), J. Appa (Zenotech) and D. Standingford (Zenotech)

December 2014

## Abstract¶

In the present study the flow field around $$65^\circ$$ delta wing is investigated using the unstructured density based solver zCFD. The simulations were carried out by solving the steady state RANS equations using the k-ω SST turbulence model at :math:‘13.3^circ’ flow angle for :math: ‘Re=6.0e06’ (NASA) and :math:’Re=3.0e06’ based on MAC. Within this analysis the numerical solutions are compared against wind tunnel results performed at NASA and DLR.

## Geometry Specification¶

The geometry has been generated using the analytical definition available in the reference (Chu and Luckring). For the present study two sets of simulations were performed: (1) Comparison against the experiment performed at NASA and (2) Comparison against the experiment performed at DLR as part of the VFE 2 project.

Delta wing geometry

## Results¶

Steady state RANS, SOLAR - octree mesh (30M cells), $$Mach=0.4$$, $$Re=6.0e06$$ (based on MAC = 0.3268 m)

$$\circ$$ Large Radius - Validation against NASA Wind Tunnel Experiment

$$\circ$$ Sharp Radius - Validation against NASA Wind Tunnel Experiment

$$\circ$$ Large (right) and Sharp radius (left)