DLR-F5

(H. S. inspecting Acenaphtene transition visualization in the wind tunnel)

Introductory picture gallery
         Image 1:

Inlet flow parameters for CFD boundary conditions simulation, with a fine resolution of the measured tunnel wall boundary layer, see detail.Image shows color fringes distribution of flow velocity component in the x direction.

Image 2:

Exit static pressure data modelled from experiment. Spanwise gradient results from downstream close location of splitter plate flap.

Image 3: 

Model switch function indicating transition from laminar flow (here: black), to turbulent flow (here: purple). All side walls have turbulent flow boundary layers.

Image 4:

Analytically modelled pressure distribution for development of inverse design methods, see Reference


This is a compilation and illustration of software and data to create boundary conditions of the aerodynamic and fluid mechanic test example DLR-F5, a generic wing surface which has been investigated experimentally in the Göttingen transonic wind tunnel and has subsequently been used for development of CFD codes. 

Test case for CFD analysis codes development

For the definition as a test case see the AGARD report

To compute wing surface coordinates and transition location (see image 3, above) download the files and read the comments. See the details in images for the wing root at the leading edge, at the trailing edge and for the wing tip, (click on graphics to enlarge):

Wing DLR-F5 surface grid, details

To compute the data in the inlet and exit plane (see images 1, 2, above), download the files and read the comments.

Measured pressure distribution

For comparison with CFD flow simulation at the test case conditions see the measured data of pressure coefficient.

Test case for aerodynamic inverse design and optimization development

The case study also serves as a  test case for inverse  aerodynamic design and optimization methods: The pronounced wing root fillet on the tunnel side wall and measured pressure data there pose a challenge to 3D configuration design. A surface pressure data model (see image 4, above) on the wing is derived from the experiments.


Questions? e-mail helmut.sobieczky@dlr.de