Sponsored by the Applied Aerodynamics TC
in collaboration with the Royal Aeronautical Society
2-Day Workshop before the AIAA AVIATION 2022 Conference
Chicago, IL USA
25-26 June 2022
NASA Common Research Model (CRM)
The Challenge
Predict the effect of shock-induced separation on the variation of lift and pitching moment
with increasing angle- of-attack at transonic conditions.
Flow conditions dominated by shock-induced separation represent a significant portion of the flight regime critical
to aircraft safety and government certification regulations.
All too often, anomalies in this flight regime are not discovered until flight test,
resulting in expensive and time-consuming campaigns to "fix" associated issues.
CFD can be far more efficient than wind tunnels in simulating the forces and moments
of an elastic airplane at flight Reynolds number, but to be of practical use,
CFD must be shown to adequately model the development and progression of shock-induced separation
with increasing angle-of-attack in this portion of the flight envelope.
Results from DPW-6. Only five solutions match test data beyond Pitch Break. CAN YOU?
Objectives
To build on the 20+ years of success of the AIAA Drag Prediction Workshop series.
To assess the state-of-the-art computational methods as practical
aerodynamic tools for aircraft force and moment prediction of industry
relevant geometries.
To provide an impartial forum for evaluating the effectiveness of
existing computer codes and modeling techniques using Navier-Stokes
solvers.
To identify areas needing additional research and development.
General Information
This
workshop is open to participants worldwide. Efforts will be made to
ensure representation from all areas of industry, academia and
government laboratories.
Participation
in the CFD studies is not required to attend the workshop. Everyone is
welcome!
Open
forums will be included in the workshop to discuss the solutions and
modeling techniques.
Results
will be made available after the workshop in a report and on the DPW
website.
A nominal
registration fee will be required for attendance.
AIAA
membership is not required.
Notification of Updates
Send email to request
notification of updates to the website, geometry and release of grids:
dpwaiaa@gmail.com
Dates
Release Geometry
13 April
2021
Release Standard Grids
1 September
2021
Notice of Intent to Participate Due
15 January
2022
Abstract Deadline
1 April
2022
Data Submittal Deadline
1 May
2022
Workshop
25-26 June
2022
Workshop registration will be handled through normal AIAA procedures.
Workshop presentations will not be official AIAA papers;
however, several participants will be invited to support a special session
on shock-induced separation prediction to be held
during the AIAA SciTech Meeting, January 2023.
DPW-7 will focus on the NASA CRM Wing- Body configuration with prescribed static aeroelastic wing twist.
Results will be compared to high-quality wind-tunnel data from multiple facilities.
Required
Case 1: Grid Convergence Study
Case 2: Alpha Sweeps at Constant Re
Case 3: Re Sweep at Constant CL
Optional
Case 4: Solution-Adapted Grid
Case 5: Beyond RANS: URANS, DDES, WMLES, Lattice-Boltzmann, etc.
Unstructured, Overset, and Multi-Block grids were released on 8 October 2021.
Additional grids will be made available soon.
Any additional grids used to create submitted results must be provided to the DPW Committee.
