About PADRI-2017 The main objective of the Open Workshop PADRI2017 (http://congress.cimne.com/padri-2017/frontal/default.asp) is to find candidate flow control technologies and optimization strategies that can minimize shock wave and interference drag in the strut-wing junction region in cruise condition. The ECCOMAS Industry Interest Group (IIG) is actively promoting the ECCOMAS Advanced Workshop PADRI. The high level objective of this worksho…

About PADRI-2017
The main objective of the Open Workshop PADRI2017 (http://congress.cimne.com/padri-2017/frontal/default.asp) is to find candidate flow control technologies and optimization strategies that can minimize shock wave and interference drag in the strut-wing junction region in cruise condition.
The ECCOMAS Industry Interest Group (IIG) is actively promoting the ECCOMAS Advanced Workshop PADRI. The high level objective of this workshop is to strengthen the ECCOMAS industrial group and to develop contact between ECCOMAS and the DGs of the European Commission. 
PADRI2017 proposes a test case reproducing, even at low velocity, a typical shock wave pattern in the region of the junction strut-wing of an aircraft. In order to simplify the problem, some constraints have been setup, so that the geometrical modifications should be confined to a defined small region around the strut-wing junction, and the objective function is clearly explained in order to ensure computational data results comparisons across all the technology solutions and participants. A computational platform will allow all participants to compare on outputs and formats selected by organizers their respective data results installed on a Database with respect to the reference (baseline) and to show the benefit of the chosen flow control technology.
The workshop intends to contribute to fill the gap between the different technology models and their application.
Technical Description of the Test Case 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.;

Mach= 0.72
Angle of attack= 1
Reynolds/length= 7.1.106m1
Altitude= 30000 ft
Atmosphere= ISA+0
Pressure= 30089.59 Pa
Temperature= 228.71 K

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. 
Conference organized by CIMNE Congress Bureau.