Effects of Surface Roughness on Shock-Wave/Turbulent Boundary-Layer Interaction at Mach 4 over a Hollow Cylinder Flare Model
Abstract
Although it is understood that surface roughness can impact boundary layer physics in high-speed flows, there has been little research aimed at understanding the potential impact of surface roughness on high-speed shock-wave/boundary-layer interactions. Here, a hollow cylinder flare model was used to study the potential impact of distributed surface roughness on shock-wave/boundary-layer interaction unsteadiness. Two surface conditions were tested—a smooth steel finish with an average roughness of 0.85 μm and a rough surface (3K carbon fiber) with an average roughness value of 9.22 μm. The separation shock foot from the shock-wave/boundary-layer interaction on the hollow cylinder flare was tracked by analyzing schlieren images with a shock tracking algorithm. The rough surface increased boundary layer thickness by approximately a factor of 10 compared to the smooth case, significantly altering the interaction scaling. Despite normalizing results, based on this boundary layer scaling, the rough surface case still exhibited mean shock foot positions further upstream more than the smooth surface case. Power spectra of the unsteady shock foot location data demonstrated that the rough surface case exhibited unsteady motion with attenuated energy relative to the smooth-wall case.
Document Details
- Document Type
- Pub Defense Publication
- Publication Date
- Aug 23, 2022
- Source ID
- 10.3390/fluids7090286
Entities
People
- Cary Smith
- Christopher S. Combs
- Elijah J. Lalonde
- Eugene N. Hoffman
- John D. Schmisseur
- Mark T. Gragston
- Mason Pohlman
- Matt Garcia
Organizations
- Air Force Office of Scientific Research
- National Aeronautics and Space Administration
- Office of Naval Research