HLPW6: Scale-Resolving Simulations (SRS) Technical Focus Group

Welcome to the SRS TFG page for AIAA High Lift Prediction Workshop 6 (HLPW6). This group explores scale-resolving CFD methods (including WMLES and HRLES) for high-lift configurations, focusing on accuracy, affordability, grid requirements, and turbulence modeling for industrial applications.

Join the TFG Distribution List

• Email: konrad.a.goc@boeing.com

Meeting Schedule and Access

• Bi-weekly on Tuesdays at 7:00 am PST / 10:00 am EST
• Meeting link (Teams):
  https://gov.teams.microsoft.us/l/meetup-join/19%3agcch%3ameeting_fc2077d8ffb4482fb80c13707d1515fa%40thread.v2/0?context=%7b%22Tid%22%3a%22bcf48bba-4d6f-4dee-a0d2-7df59cc36629%22%2c%22Oid%22%3a%22715af819-fa5f-480a-b2f0-dc313272648d%22%7d

Participation Types

• Active participant (attend meetings and run simulations)
• Limited participant (attend meetings and run some simulations)
• Observer (attend meetings only)

Group Leadership

• Konrad Goc — Boeing (Co-Leader; emphasis on LES methods)
• Eduardo Molina — Embraer (Co-Leader; emphasis on HRLES methods)
• Daniel Heathcote — Aurora Flight Sciences (Deputy Leader)

Schedule and Milestones

• Test Case 1 — CRM-HLS: January to May 2026
  Case hub: https://aiaa-hlpw.org/HLPW6/cases
  Looking for participants to run WRLES/DNS
  Mini-Workshop 1: AIAA Aviation 2026 (8–12 June, San Diego, CA)
  Session time: 5:30 pm PDT, Room Harbor B (hybrid option planned)

• Test Case 2 (TBD) — ONERA LRM 2.3 or 2.4: June 2026 to January 2027
  Focus: Laminar–turbulent transition on slat; flap lift overprediction
  Mini-Workshop 2: AIAA SciTech 2027 (11–15 Jan, Orlando, FL)

• Test Case 3 (Tentative) — CRM-HL Take-off Configuration: February 2027 to June 2027

• HLPW6: AIAA Aviation 2027 (7–11 June, San Diego, CA)

Meeting Format

• Leadership updates (short)
• Participant updates (majority of time) — verbal and prepared updates welcome
• Open discussion

Presenter slide sharing:

• Please include and share your presentation with:
  • heathcote.daniel@aurora.aero
  • eduardo.molina@embraer.com.br
  • konrad.a.goc@boeing.com
• Slides shared during the bi-weekly meetings will not be published outside the workshop.
• Slides should include numerical force/moment values listed on them to facilitate cross-plotting by the TFG Leadership Team

Key Questions

General

1. Are there meaningful distinctions in predictive accuracy among scale-resolving methods (e.g., WMLES, DES, LBM)? What are the relative strengths/weaknesses for maximum lift and key flow features (wing root separation, slat bracket wakes, flap separation)?
2. What is the state of affordability of scale-resolving methods for high-lift prediction? Are they feasible for routine industrial use on modern compute hardware?
3. Which turbulence model choices/frameworks are needed to systematically improve high-lift flow prediction accuracy?
4. What grid distribution/topology/density choices are required for accurate high-lift predictions? What are the implications for near-wall grid size for different SRS methods (e.g., WMLES/HRLES running at y+ in the log layer)?

Test Case Specific

• TC1 (CRM-HLS, Jan–May 2026):
  Can SRS methods provide a high-fidelity reference solution set, including solutions on highly resolved meshes (potentially WRLES/DNS)?
• TC1/TC2.1 (HLPW5 TC2.3/4, 3–4 AoAs near stall, Jun 2026–Jan 2027):
  How should SRS methods handle laminar–turbulent transition, especially on the slat? How can the predicted leading-edge boundary layer state be validated (e.g., using experimental or DNS/WRLES data)?
• TC2.2 (HLPW5 TC2.3/4, 3 AoAs in linear CL range, Jun 2026–Jan 2027):
  How can we improve accuracy at low angles of attack, where flap separation misprediction often leads to large lift errors?
• TC3 (likely ONERA takeoff config, Feb–May 2027):
  Can SRS methods reliably predict aircraft drag at low angle of attack?

Test Case 1: CRM-HLS Overview

• Simplified high-lift configuration developed via Boeing/University of Washington collaboration
• Geometry:
  • Finite span wing
  • Full-span slat
  • Partial span flap
  • Y=0 symmetry plane
• Reynolds number: 3.55 million based on chord (ReC)
• Built to target slat bracket wake separation on the second outboard bracket
• No experimental data yet (potentially mid-workshop)

Resources and Support

• Tecplot complimentary licenses available for workshop participants
  Contact: Gibson Adams — g.adams@tecplot.com
• Need grids to run on? Contact TFG leadership.
• Note: Grid characteristics may differ between HRLES and WMLES; pay attention to gridding strategies appropriate for your selected method.

Presentations from Bi-Weekly TFG Meetings

• TFG Meeting 2: 2/10/26
• Kickoff Meeting: 1/27/26

HLPW6 Website

• Main site: https://aiaa-hlpw.org/
• Cases page: https://aiaa-hlpw.org/HLPW6/cases
• This TFG page: https://aiaa-hlpw.org/HLPW6/TFG_SRS

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Last updated: 2026-02-10