Accession Number:

ADA564713

Title:

Supersonic Inlet Flow Control Using Localized Arc Filament Plasma Actuators

Descriptive Note:

Final rept. 1 Jul 2009-28 Feb 2011

Corporate Author:

OHIO STATE UNIV COLUMBUS DEPT OF MECHANICAL AND AEROSPACE ENGINEERING

Personal Author(s):

• Samimy, Mo
• Webb, Nathan
• Clifford, Christopher

Report Date:

2011-05-10

Pagination or Media Count:

37.0

Abstract:

Shock WaveBoundary Layer Interactions SWBLIs occur in many applications of interest to the U.S. Air Force and could pose significant problems depending on the specific application. This study has undertaken to investigate the use of Localized Arc Filament Plasma Actuators LAFPAs to control SWBLIs with the objective of mitigatingeliminating separation. Initial experiments were carried out in a small Mach 2 tunnel with compression ramp. The results showed that the LAFPAs are capable of significantly energizing the flow within the interaction region when located upstream of the reflected shock. The maximum control authority was found to be exercised when the LAFPAs were operated at a Strouhal number of 0.03. This frequency is similar to that at which the reflected shock oscillates in unforced SWBLIs. Therefore, LAFPAs are believed to manipulate the natural instability associated with the reflected shock oscillation. The success of the preliminary experiments motivated the design of a new, larger, more flexible facility that utilize a Variable Angle Wedge to generate the impinging shock wave for SWBLI. This facility is capable of easily generating a wide range of SWBLI strengths. The research is currently on-going.

Descriptors:

• *ACTUATORS
• *SUPERSONIC INLETS
• BOUNDARY LAYER
• FILAMENTS
• INTERACTIONS
• MACH NUMBER
• OSCILLATION
• SHOCK WAVES
• STROUHAL NUMBER
• SUPERSONIC FLOW

Subject Categories:

• Machinery and Tools
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE