Strut wing test case is based on an unformatted geometry of an aircraft with upper wing, which is supported by a strut. The geometry includes the entire aircraft with tail and empennage, but simplifications can be applied if necessary, discarding the empennage and tail, or considering symmetry.

The flow conditions are summarized as: Mach 0.72, angle of attack 1º, Reynolds number over length 7.1x106 m-1, cruise altitude 30000ft on an atmosphere ISA+0 with pressure 30089.59 Pa, and temperature 228.71K.

The main focus should be put on the region of the strut-wing junction in the mentioned cruise conditions, analyzing the shock wave and the interference drag in this particular region.

The definition of the best flow control device, which helps to diminish the shock and the drag, is the main objective and should be demonstrated through the analysis of the simulation results.

Aerospace Europe web platform (www.aerospace-europe.eu) will be used to enable a flexible and easy communication and handling of the workshop related information and data.

The initial information released by AIRBUS, and to be used by the contributors is already available for downloading. Please follow the link to “Case Studies”, and “A common platform for validation of aircraft drag reduction technologies”.

A database will be set up within the Aerospace Europe web platform. It will store the results from each contributor, classified according the criteria defined by the evaluation purposes.

Each contributor will have its own space, but will be able to consult and compare with results by other contributors. The information, data and results uploaded in this database will be the main source of comparison during the workshop sessions. It will complement the presentations by each contributor.