LINEAR MODAL AND NON-MODAL INSTABILITY ANALYSES OF HIGHSPEED LAMINAR SEPARATED FLOW OVER COMPLEX GEOMETRIES PART I: ALGORITHMIC DEVELOPMENTS
Abstract
It is proposed to analyze modal and non-modal linear instabilities developing in the boundary layer over a hollow-cylinder flare and on a modified Oberkampf (sliced-cone/wedge) body, with the aim of identifying, predicting and controlling laminar-turbulent flow transition on these geometries at supersonic and hypersonic conditions, respectively. Motivation is provided by parallel ongoing experimental efforts at the University of Tennessee Space Institute and the Purdue School of Aeronautics and Astronautics, compounded by the absence in the literature of results obtained by employing the (appropriate for both geometries) global linear analysis theoretical framework; the proposed effort will be the (worldwide) first of its kind for both configurations.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 11, 2021
- Source ID
- FA86552017022
Entities
People
- Vassilios Theofilis
Organizations
- Air Force Office of Scientific Research
- United States Air Force