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A Computational Framework for Simulating Flow around Hypersonic Re-Entry Vehicles

A Computational Framework for Simulating Flow around Hypersonic Re-Entry Vehicles . Current challenges in computational aerothermodynamics (CA) Efficient generation of unstructured grids to resolve complex geometry Higher order discretization schemes for shock capture

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A Computational Framework for Simulating Flow around Hypersonic Re-Entry Vehicles

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  1. A Computational Framework for Simulating Flow around Hypersonic Re-Entry Vehicles • 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 David Stroh, Anthony Marshikand GauthamKrishnamoorthy,UND Chemical Engineering • 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

  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 transportmodel (> 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

  3. Accomplishments Task 3 • Training of UGRAs • Tasks: • Task 1: Laminar flow over bluntcone • 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 Radiativeheat transfer (in progress) Task 2 • Newer transitional models are very promising! • Investigating sensitivities to turbulence • boundary conditions Spherically blunt cone

  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

  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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