Multi-scale Modeling of Unsteady Shock-Boundary Layer Hypersonic Flow Instabilities
Abstract
We discuss a new approach for modeling boundary layer physics in shock-wavedominated flows around highly swept and slender bodies with attached fins through the use of advanced hypersonic aerodynamic tools to predict transition pathways and unsteady aerodynamics for low hypersonic Mach numbers relevant to Navy threats. The proposed effort is the first of its kind to assess the importance of non-continuum, kinetic effects through the use of particle, kinetic simulations combined with modern global modal linear stability analysis as well as to quantify instability phenomena arising in spatially inhomogeneous laminar separated flows. The proposal builds on very recent work that has demonstrated the power of this approach by predicting the presence of lambda shocklets emerging from the recirculation region and the self-repeating diagonal structures between the contact surfaces due to expansion and compression waves as being part of one and the same amplitude function of a damped, global mode of laminar separation of flow over a double cone.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 29, 2020
- Source ID
- N000142012195
Entities
People
- Deborah Ann Levin
Organizations
- Office of Naval Research
- United States Navy
- University of Illinois Urbana–Champaign