Announcement
by admin | Mon, 02/23/2009 - 12:06The
AIAA Supersonic Shock-Boundary Layer Interaction (SBLI) Workshop
Sponsored by the Applied Aerodynamics TC
January 2010
New
February 3, 2010
Most of the presentations from the workshop have been uploaded.
OBJECTIVES
• To assess the state-of-the-art computational methods for predicting incident shock boundary-layer interactions for high speed inlet flows.
• To provide an impartial forum for evaluating the effectiveness of current computer codes and modeling techniques using Navier-Stokes solvers
• To identify areas needing research and development
FOCUS
• The focus of this workshop is on the assessment of the current capability to predict complex flow fields involving incident shock boundary-layer interaction.
• Shock boundary-layer interaction data will be furnished by the Air Force Research Laboratory/Air Vehicles Directorate and the UFAST (need proper affiliation here)
• A statistical framework will be used to assess the results.
GENERAL INFORMATION
• This workshop is open to participants world-wide. Efforts will be made to ensure participation from all sectors of the fluid dynamic community.
• Attendance at the workshop is not contingent on submission of calculations.
• Results will be made available after the workshop and on the SBLI website.
• AIAA membership is not required for attendance
• A nominal registration fee will be required for attendance.
SBLI WORKSHOP CHALLENGE PROBLEMS
• There will be four SBLI interactions that can be computed for the workshop. Because of the complex nature of the flow fields involve the challenge flow, two cases will be open (i.e., the data will be available before the work shop) and two will be blind (i.e., the data will not be available before the workshop). All participants are encouraged to attempt the blind cases.
• The challenge problems are organized with increasing shock strength and geometric complexity; the first problem will involve a shock generator that spans the wind tunnel test section and the remaining problems will involve a shock generator located in the center of the test section but does not span it.
• Workshop presentations will not be official AIAA papers, but several participants will be invited to support a special session on incident shock boundary-layer interaction at the AIAA Applied Aerodynamics summer meeting.
GRIDS
• Computational grids will not be provided. Each participant is encouraged to generate grids that are best suited to their flow solver.
• Computational grids used to create submitted results must be provided to the SBLI Committee
The four challenge problems are:
| Conditions | ||||
| # | Type | Mach | Wedge angle | Data Source |
| 1 | Open | 2.25 | 8 | IUSTI Marseille (UFAST) |
| 2 | Open | 2.75 | 7.75 | University of Michigan |
| 3 | Blind | 2.75 | 10 | University of Michigan |
| 4 | Blind | 2.75 | 12 | University of Michigan |
DATES:
| Geometries & Flow Conditions Available | 16 January | 2009 |
| Open Problems data available | 1 February | 2009 |
| Abstracts Due | ||
| Acceptance notification | 2Q | 2009 |
| Final Papers Due | 4Q | 2009 |
| Registration | 4Q | 2009 |
| Workshop | January | 2010 |
Committee
| John Benek | Air Force Research Laboratory/Air Vehicles Directorate |
| Jon Tinapple | Air Force Research Laboratory/Air Vehicles Directorate |
| Charles Hirsch | Numeca, Belgium |
| Holger Babinski | University of Cambridge, UK |
| James Luckring | NASA/Langley Research Center |
| James DeBonis | NASA/Glenn Research Center |
| James Chung | NAVY |
Last Update: 13.Mar.2009 08:07
