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Submission of Contributions

The workshop is aimed to present and compare the resolution of the proposed test case. The test case is focused on the reduction of drag using flow control devices in a strut-wing aircraft configurations, details are provided here

Authors are invited to directly register, indentifying themselves as “Contributors”. If possible, please submit an abstract briefly describing the proposed solution and results. Once the contributors have the results available, they can upload them on the conference website

To be able to submit an abstract, you have to first register.

Further information regarding the objectives and description of the test case is available here

Files related to the definition of the test case are available here

Results to be provided are as following:

CFD solution for the velocity (Mach number)

CFD solution for Pressure (aimed to identify the position of shock wave)

CFD solution for Cd_wave (Please refer to the description of the test case to know details about how to calculate Cd_wave)

2D section of the velocity solution at the following positions defined below

2D section of the pressure solution at the following positions defined below

2D section of the Cd_wave solution at the following positions defined below

All the above listed results should be provided without (baseline) and with the use of a Flow Control Device. If possible the comparison as increment respect to the baseline should also be provided.

If optimization methods have been applied as part of the solution, please provide the convergence history of the objective functions.

Assessment of the cost of installed the selected flow control device

Sections to be provided:

- Respect Z axis, 3 sections between 0.87 and 1.07 respect the reference origin (as provided in the files). Positions 0.87, 0.97, 1.07.
- Respect Y axis, 10 sections between 12 and 16.5 respect the symmetry plane. Positions 12, 12.5, 13, 13.5, 14, 14.5, 15, 15.5, 16, 16.5.
- Respect Y axis, 3 sections between 16.8 and 17.8 respect the symmetry plane. Positions 16.8, 17.3, 17.8.  

 


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