Fluid Structural Thermal Interactions (FSTI) in Hypersonic Flow
Abstract
The proposed work envisions a new multi pronged approach to advance the current state of the art for fluid structural thermal interactions (FSTI) that occur in a hypersonic flow environment. The objective of the proposed work is to obtain fundamental insights into the physics of the FSTI over a wide range of Mach numbers spanning supersonic through hypersonic regimes by designing and executing key experiments and by developing theoretical-computational models of varying fidelity that capture the physics of the interactions at various levels of detail. The project goal is approached by a set of complementary experimental and computational efforts that mutually augment one another. The experiments will be conducted in multiple facilities that include NCSU’s variable Mach number wind tunnel facility (M = 4.0), AEDC Tunnel 9 (M = 8, 10, 14), and possibly NASA Langley’s 31 inch Mach 10 facility that provides redundant measurements at Mach 10. Whereas the NCSU facility will be employed to provide very detailed insights into the FSI mechanisms that will feed into the models, other facilities will provide Mach number scaling of the interactions and the thermal component of interactions. Computational simulations will involve development a high fidelity computational FSTI infrastructure for simultaneous treatment of shock laden reacting and non reacting flows, heat transfer, its effects on the structure, and related material limits. Case studies will include a combination of high fidelity scale resolving simulations as well as low order models that capture the main physics of the interactions to help inform future experimental campaigns and data reduction methodologies.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 14, 2022
- Source ID
- FA95501910313
Entities
People
- Venkateswaran Narayanaswamy
Organizations
- Air Force Office of Scientific Research
- North Carolina State University
- United States Air Force