Datasets / Shock Generation and Control Using DBD Plasma Actuators Project


Shock Generation and Control Using DBD Plasma Actuators Project

Published By National Aeronautics and Space Administration

Issued about 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Shock-wave/boundary-layer interactions (SWBLI) pose challenges to aeronautical engineers because they create regions of adverse pressure gradients as a result of the discontinuous change in conditions across the shock. This shock-induced pressure gradient is a common factor for both flow separation in supersonic inlets and high stagnation pressure losses on transonic wings, factors which are known to reduce performance and efficiency. These affects can be corrected with appropriate forms of flow control. Innovative Technology Applications Company (ITAC) and University of Notre Dame (UND) propose the use of electrohydrodynamic (EHD) plasma actuators to control the affects of SWBLIs for two types of problems, one involving boundary layer separation and the other transonic wave drag. We propose to use plasma actuators near the region of the SWBLI to eliminate or delay the onset of separation in supersonic inlets while using plasma-based shock control methods to reduce the stagnation pressure losses on transonic airfoils. The advantages of the dielectric barrier discharge (DBD) actuators are that they are fully electronic, contain no moving parts, surface mountable, minimally intrusive, can be turned off when not needed, and electrically re-configurable for optimal control in dynamic flow conditions.