Accession Number:

ADA463793

Title:

Surface Discharges for High-Speed Boundary Layer Control (Postprint)

Descriptive Note:

Conference paper

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE

Report Date:

2006-01-01

Pagination or Media Count:

11.0

Abstract:

Surface plasma discharges have been shown to be effective in altering laminar boundary layers, Judicious choice of electrode shape can create a discharge that emulates a wedge or a bump, The virtual wedge discharge has been shown to create a local pressure rise with potential applications to vehicle control. The virtual bump creates a lesser pressure rise, but strong distortion of the boundary layer. In the current work the effect of the bump discharge on laminar shock boundary layer interactions is explored. Laminar shock boundary layer interactions are created with an impinging shock on a flat plate at a freestream Mach number of 5. The primary instrumentation is a low-modulus elastomer doped with a pressure-sensitive dye, Intensity distributions from the dye are imaged to interrogate the surface pressure. Displacement of surface markers provides surface shear information. Results show the presence of Gortler vortices in the reattaching shear flow. The Gortler vortices are also evident in temperature-sensitive paint images.

Subject Categories:

  • Coatings, Colorants and Finishes
  • Elastomers and Rubber
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE