Slide #1.

A Computational Framework for Simulating Flow around Hypersonic Re-Entry Vehicles David Stroh, Anthony Marshik and Gautham Krishnamoorthy, UND Chemical Engineering  Current challenges in computational aerothermodynamics (CA) • Efficient generation of unstructured grids to resolve complex geometry • Higher order discretization schemes for shock capture • Laminar to turbulence transition models • Reactions due to dissociation of air • Thermodynamic non-equilibrium • Spectral radiation • Solid deformation due to ablation  Long term goal: Development of add-on modules/functions and best practice guidelines that extends the capabilities of commercial codes to study (CA) problems  Short term goal: • Infrastructure: Software licenses (ANSYS FLUENT, ANSYS AUTODYN) • Sandia’s DAKOTA tool kit for uncertainty quantification • Training of students • Software validation of unit problems
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Slide #2.

Relevance to NASA • • • Directly relevant to the mission of NASA’s Division of Atmospheric and Planetary Sciences. A hierarchial validation approach ranging from unit problems to more complex problems Validations accomplished through comparisons against experimental data and predictions from NASA’s in-house CA codes:  LAURA: Hypersonic flows  ANSYS FLUENT has additional transitional turbulence modeling options  SAS and embedded LES options can resolve global instabilities and turbulent structures  Additional “vibrational temperature” transport equation will be solved  NEQAIR: 1D line-by-line Radiative transport model (> 200,000 spectral intervals)  2D/3D calculations in ANSYS FLUENT account for shock curvature  Tighter coupling with fluid flow  Speed up spectral calculations by reducing it to a few 100 intervals  CMA, FIAT: Material response  Tighter coupling with fluid dynamics  Stronger deformations can be handled through the explicit solver in ANSYS AUTODYN
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Slide #3.

Accomplishments • Training of UGRAs • Tasks: Task 1: Laminar flow over blunt cone Task 2: Transitional flow over flat plate Task 3: Surface heat transfer and real gas over a sharp cone Backward and forward facing steps Flow over Mach 20 spherical blunt cone Task 4: Chemistry Task 5: Plasma torch problem for Radiative heat transfer (in progress) Task 3 Task 2 •Newer transitional models are very promising! •Investigating sensitivities to turbulence boundary conditions Spherically blunt cone
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Slide #4.

Student involvement • Use of commercial tools speeds up the learning process. • Two UG research assistants (David Stroh and Anthony Marshik) were employed full-time over Summer 2011 – They were trained on the numerical aspects of computational fluid dynamics – They developed a theoretical understanding of boundary layer flows – They developed and demonstrated extensive familiarity with the commercial code ANSYS FLUENT • Manuscript in preparation for submission to AIAA Journal of Spacecraft and Rockets
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Slide #5.

Future plans for proposals • NASA NRA – Research Opportunities in Aeronautics • Air Force BAA (Aerospace, Chemical and Material Sciences) - 2012 • NSF Fluid Dynamics Program (Feb 2013)
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