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
November 11, 2009
UofM_faq.txt added to UofM data section.
September 4, 2009
The files geometry_wind tunnel.pdf and 807_IUSTI_final_report_UFAST_2009_v2.pdf were added to the UFAST wind tunnel data section.
August 31, 2009
The Mach number for the UFAST data has been corrected in the table below.
August 19, 2009
The following email was sent to all users who have a valid email registered on this web site.
Dear colleague,
Thank you for your interest in the AIAA Shock Boundary Layer work shop. We are currently making final preparations for the workshop which will be held at the Aerospace Sciences Meeting in Orlando, Florida, on Friday, 8 January 2010.
As part of this effort, we are trying to determine the number of attendees and presenters and which solutions will be presented. Please send your response to Dr. Casimir Suchyta (casimir.suchyta.ctr at wpafb.af.mil) by 11 September 2009. To simplify your response, we have provided a convenient table in the attached file.
Thank you for your interest. I am looking forward to seeing your results.
Best regards,
John A. Benek
May 28, 2009
Corrections to the UFAST readme.txt and UFAST_Data.tar_.gz file have been uploaded. The source of the data has been corrected and Mach number and pressure of the experiment have been changed (Mach=2.25 and the stagnation pressure in the free stream flow is 50.5 kPa). The names of the data files have been changed to reflect the corrected Mach number but the flow data has not changed.
May 7, 2009
A revision to the UofM data has been uploaded. The new data is containted in the file UM_data_rescaled.tar_.gz.
The original UofM data contained a small systematic velocity bias in some of the measurements that was a result of an inherent limitation of the technique used to measure the velocity fields. (Please see the bias.txt file for a discussion of this bias.) The revised data that are now provided have been rescaled to remove this systematic bias.
The UFAST Wind Tunnel data, needed for case 1 has been uploaded. Click on the "Numerical and Experiment Database" link on the left and then click on the "UFAST Wind Tunnel Data" link.
The UofM Wind Tunnel data, needed for cases 2, 3, and 4 have been uploaded. Click on the "Numerical and Experiment Database" link on the left and then click on the "UofM Wind Tunnel Data" link.
Instructions for preparing and uploading results have been added. Click on the "Instructions" link on the left side of the page. Click on "Data Format" for instructions on preparing your results can click on "Uploading Data" for instructions on uploading the data.
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
