Investigation of 3D Shockwave Boundary Layer Interaction and Related Phenomena for the STORT Flight Program
Abstract
Scientific flight tests are crucial for gaining fundamental knowledge necessary to develop hypersonic systems. The overall objective of this research is to establish such knowledge for transitional/turbulent 3D shockwave boundary-layer interactions (SBLIs) and related phenomena on the STORT flight experiment. These additional phenomena include boundary-layer transition, fin-body junction flows, shock-shock interaction (SSI) and fluid-structure interaction due to vibration. A collaborative approach, consisting of wind tunnel experiments, local heat flux correlations, direct numerical simulations (DNS), stability theory and state-of-the-art analysis will be employed for both pre- and post-flight efforts in close collaboration with DLR. The research will be specifically tailored to complement DLR efforts in order to maximize the extraction of fundamental physics. Experiments center around spatially and temporally resolved measurements at Mach 5 for a hollow cylinder and flat plate with a geometrically scaled fin. This is chosen to isolate the influence of base curvature while allowing high spatial resolution in the fin region. These experiments directly complement the 1:2 scale STORT model and flat plate tests planned at DLR. Local correlations will be employed to assess heat flux in the SBLI/SSI regions and especially near the fin body junction for all cases (UArizona, DLR and flight). High fidelity DNS and stability theory will be performed to investigate transition physics and its impact on the SBLI topology, unsteadiness and heat flux over a range of wind tunnel (both UArizona and DLR) and flight conditions. The vast amount of experimental, computational and flight data will be analyzed using state-of-the-art post-processing techniques. The outcome will be a unique contribution to the understanding of 3D SBLIs and related phenomena in flight conditions as well as improved prediction methodologies based on ground tests and simulations for a large range of Mach numbers.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 21, 2022
- Source ID
- FA95502110018XX0
Entities
People
- Jesse C. Little
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Arizona