DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
ADA464389
Title:
Reactive Flow Control of Delta Wing Vortex (Postprint)
Descriptive Note:
Conference paper
Corporate Author:
OHIO UNIV ATHENS DEPT OF ELECTRICAL AND COMPUTER ENGINEERING
Report Date:
2006-08-01
Pagination or Media Count:
27.0
Abstract:
In this paper, the reactive flow control of delta wing leading edge vortices using along-core pulse width modulation PWM flow injection is presented. Leading edge vortices on the upper surface of a delta wing can augment lift. Manipulating breakdown points of leading edge vortices can effectively change the delta wings lift and drag and generate attitude control torque. In this paper, a dynamic model of active flow control of vortex break down points is identified from wind tunnel data using a model scheduling method. Based on the identified model, a closed-loop active flow controller is developed. Simulation and real-time wind tunnel test show that the closed-loop controller can effectively manipulate the upper surface pressure of the delta wing, which indicates the closed-loop controller can effectively control vortex breakdown points.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE