Low-frequency, spanwise oscillation in a finite-width cavity at Mach 1.5
Abstract
A joint experimental–computational program examined low-frequency, spanwise oscillations in supersonic flow over a finite-width cavity. Lowpass-filtered rear wall surface pressure revealed that shear layer impingement was most often biased to one side of the wall, switching sides at a frequency two orders of magnitude below resonance. Therefore, a bifurcation into two spanwise-asymmetric, mirrored, quasi-steady states could be defined. The states were described by biased impingement/ejection near the rear wall, asymmetry of the shear layer, and centrifugal inner-cavity flow. Resonance amplitudes were also found to be spatially modulated by the low-frequency flow switching. A yawed inflow was found to force one of the asymmetric states.
Document Details
- Document Type
- Pub Defense Publication
- Publication Date
- Jul 01, 2021
- Source ID
- 10.1063/5.0053682
Entities
People
- Aaron M. Turpin
- Kenneth Granlund
- Rachelle L. Speth
- Scott E. Sherer
Organizations
- Air Force Office of Scientific Research
- Air Force Research Laboratory
- North Carolina State University