DLR-F6 Aircraft

Navier-Stokes calculations with EDGE for the DLR-F6 aircraft configuration using different turbulence models.

The simulations were carried out for angles of attack in the range of [-3°, 1.5°] at a Mach number of 0.75 with three meshes for the wing-body (WB) and wing-body-nacelle-pylon (WBNP) configurations, respectively.

As an example, the above figure visualizes the pressure distribution around the WBNP model. The pictures below show flow separation on the aircraft surface, where the Spalart-Allmaras model has been employed for alpha=1° on a hybrid mesh with about 3.2 millions nodes.

[1] S-H. Peng, Numerical computation on the DLR-F6 aircraft configuration using different turbulence models. Scientific Report, FOI-R--1154--SE, 2004.

[2] S.-H. Peng and P. Elliasson, A Comparison of Turbulence Models in Prediction of Flow Around the DLR-F6 Aircraft Configuration, AIAA Paper 2004-4718.

Shia-Hui Peng, FOI/FFA, 2004.