Supersonic Aircraft Shape Design Powered by SU2 and Pointwise
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Supersonic aircraft are poised for a comeback. Current regulations do
not permit supersonic flight over land due to sonic boom noise. However,
recent advances in simulation-based design are opening the door to new
supersonic aircraft designs with reduced sonic boom impacts. The design
of these aircraft requires accurate predictions of sonic boom on the
ground and techniques for shaping the aircraft to achieve a desired boom
signature while maintaining performance.
This webinar details how Pointwise and SU2 can be used to tackle
supersonic aircraft design. Watertight surface and volume meshes for
complex geometries can be quickly generated in Pointwise and exported to
the native SU2 format.
A properly constructed mesh aids in accurately
predicting boom on the ground. Furthermore, a new script for Pointwise
can help designers generate Free Form Deformation (FFD) boxes for geometry
parameterization and shape design in SU2.
We will also demonstrate how to formulate and solve a shape design
problem in SU2,
using a continuous adjoint formulation to obtain the
sensitivities for gradient-based optimization. This includes a
discussion of proper settings for the flow and adjoint problems,
objectives and constraints, FFD design variables, and mesh deformation.
Finally, we will present optimal shape design results from
SU2 for the Lockheed Martin 1021 aircraft.
Discover How To
- Quickly generate a watertight unstructured surface and volume mesh
suitable for Euler calculations.
- Improve farfield shock capturing without the need for grid
adaptation by assembling Mach aligned structured blocks.
- Save time by creating FFD boxes for design
optimization within Pointwise.
- Easily configure SU2 for solving the Euler and adjoint Euler
equations and computing surface sensitivities for design.
- Set up a shape design problem in SU2, including formulating
objectives and constraints, FFD design variables, and mesh
- Perform optimal shape design of a supersonic aircraft for minimizing
drag with constraints.
Lockheed Martin 1021
The Lockheed Martin 1021 is one of the test cases from the
AIAA 1st Sonic Boom Prediction Workshop.
At that website you will find the technical paper
Full Configuration Low Boom Model and Grids for 2014 Sonic
Boom Prediction Workshop by J. M. Morgenstern, M. Buonanno,
and F. Marconi (AIAA Paper 2013-0647).
Also, check your computer's compatibility with the
system requirements from GoToWebinar.
A watertight unstructured surface mesh suitable for Euler calculations
was generated for the Lockheed Martin 1021 low boom supersonic transport
CFD solution computed using SU2 captures high resolution shock
structures present on the surface of the aircraft and propagating well
into the farfield.
Who You'll Meet
Travis Carrigan joined Pointwise as a senior engineer after completing
his M.S. in aerospace engineering at The University of Texas at
Arlington in May 2011 where his graduate research involved aerodynamic
design optimization. He interned at Pointwise beginning May 2008,
producing demonstration and application videos and working in technical
support, doing grid projects and quality assurance testing. During a
prior internship at Vought Aircraft Industries, Mr. Carrigan worked as a
quality engineer on the Boeing 787 Dreamliner Program. As a senior
engineer at Pointwise, Mr. Carrigan works with clients to strengthen
their computational fluid dynamics (CFD) processes by developing
interactive and automated meshing solutions.
Dr. Francisco Palacios is an engineering research associate at the
Department of Aeronautics and Astronautics at Stanford University. His
main areas of expertise include optimal aerodynamic shape design,
large-scale multi-physics CFD simulations, and numerical analysis. Prior
to his arrival at Stanford University in 2011, Dr. Palacios was research
lead for technological innovation at the Madrid Institute for Advanced
Studies and coordinator of the Airbus program “Future Simulation
Concepts”. From 2011 to 2013, Dr. Palacios was responsible for the
development of the main RANS solver for the Stanford PSAAP center, and
for the research in adjoint-based methodologies to manage the
uncertainties that are present in hypersonic combustion environments.
Currently, Dr. Palacios research is focused on supersonic aircraft
design and the development of novel shape design techniques applied to
Trent Lukaczyk is a Ph.D. candidate in the Aerospace Design Lab within
the Department of Aeronautics & Astronautics at Stanford University. His
core research interests are in aircraft design and optimization methods,
and he is currently contributing to the design of NASA's next-generation
supersonic passenger jet. This work depends on experience in various
disciplines that he gained during several internships and his
undergraduate education at Cornell University: developing meshing tools,
simulating the aerodynamics of both aircraft and automobiles, testing
those designs in the wind tunnel, and designing combustion engines.
Thomas D. Economon is currently a Ph.D. candidate in the Aerospace
Design Lab within the Department of Aeronautics & Astronautics at
Stanford University. His research focuses on the development of new
design methodologies for aerospace systems, including high-fidelity,
adjoint-based techniques for optimal shape design, as well as tools for
design at the conceptual level. He has extensive experience with high
performance computing and the development of CFD platforms, most notably
as a member of the core development team for the open-source SU2
software suite. He holds a B.S. in Aerospace Engineering from the
University of Notre Dame (2008) and an M.S. in Aeronautics &
Astronautics from Stanford University (2010).
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