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A Selection of Experimental Test Cases for the Validation of CFD Codes

The data presented in this contribution were obtained in the DLR Transonic Vind Tunnel Braunschweig.
The intent of the experiment was to provide data giving information on the developpment of the
TUB-side wall boundary layer in the presence of a typical transonic airfoil model for further in-
vestigation of the influence of the side wall boundary layer on 2-D airfoil measurements. For this
purpose boundary layer pitot pressures were measured in 13 different side wall positions around the
airfoil. Airfoil pressure distributions were obtained in several spanwise positions by sliding the
airfoil model in spanwise direction.

The test cases investigated correspond to the design flow conditions of the airfoil (Ma = 0.73,
0'. = 1.5") and to a low (.3: 0°) and a high (an 3.0") lift value at the same Mach number. For these
cases wall pressure distributions were measured on the centre slat of the top and bottom walls.
Additionally to the pressure measurements some oil flow pictures were made on the upper airfoil
surface and the adjacent wind tunnel side wall to get more insight in the structure of the flow.

In order to have well defined wind tunnel boundary conditions for the evaluation by computational
methods, the slotted top and bottom walls of the test section were closed for these specific tests.
This means, of course, that the presented airfoil pressure distributions do not correspond to free
flight conditions and are not comparable to wind tunnel results obtained in slotted or perforated
transonic test sections.