Dynamics of shock-wave/boundary-layer interactions over axisymmetric bodies
Abstract
Shock-wave/boundary-layer interactions (SBLI) constitute an important class of aerodynamic phenomena, due to its influence on unsteady scales, wall-loading, and moments to which highspeed air vehicles are subjected to. Unlike the 2D scenario, we have minimal insights into the dynamics of 3D SBLI over axisymmetric bodies, which are crucial to Naval applications including interactions involvingcontrol surfaces and vehicle fuselage, and stage and store separation scenarios. The proposed effort will study fundamental flow physics of this problem by adopting a multi-fidelity computational approach, utilizing in-house simulation and analysis suites. The flow problem will be defined as the interaction of an oblique shock impinging over a cylindrical geometry, in a supersonic freestream.The prime objectives of this effort include: (a) performing validated scale-resolved simulations of the axisymmetric SBLI utilizinga high-order computational framework, (b) identifying key properties of theinteraction including, topology of the separation zone, scaling laws, wake structures, and dominant spectra, (c) generating low order dynamical representations of the leeward separation zone using constructs of hydrodynamic stability theory and modal analysis tools, and (d) identifying potential challenges faced by state of- the-art turbulence modeling approaches in predicting the size and dynamics of the interaction zone. The results are expected to improve our understanding of this complex flow phenomena, specifically with respect to: the dependence of separation-bubble dynamics on upstream conditions, instability mechanisms that govern evolution of coherent structures influential in determining unsteady loads on the vehicle, asymmetric loading characteristics resulting from the wake structures, and insights into improving turbulence modeling of non-homogeneous SBLI with massive flow separation. These outcomes could significantly improve the reliability and accuracy of aerodynamic prediction tools integral to the air vehicle design process. Further, it could guide development of control strategies to counter performance deviations arising from asymmetry, unsteadiness, and intense wall-loading, resulting from this interaction.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Nov 21, 2023
- Source ID
- N000142412031
Entities
People
- S. Unnikrishnan
Organizations
- Florida State University
- Office of Naval Research
- United States Navy