Experimental and Numerical Investigation of Vortex Shedding of a Representative UCAV Configuration for Vortex Flow Control
Abstract
On vehicles with swept wings, leading edge vortices are created at off-design conditions, Ref. 1. The leading edge vortex generally has a beneficial effect in the form of increased lift. By controlling the location of the shed vortex or vortices, vehicle roll and pitch control may be possible. Uninhabited Combat Air Vehicles (UCAV) that utilize stealth to avoid detection suffer a radar signature increase when control surfaces are deflected. Thus, there is an advantage to be gained by limiting flap deflection by utilizing vortex flow control to change vehicle attitude. In view of this, an experimental and numerical investigation was conducted on a representative UCAV configuration to define the flowfield and investigate methods to control vortex location, and ultimately, vehicle attitude. In view of this, a test program was carried out to identify the flow features of a representative UCAV configuration and utilize a simple blowing jet near the nose of the vehicle to attempt vortex flow control.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2000
- Accession Number
- ADA382837
Entities
People
- Doug R. Hall
- Terence A. Ghee
Organizations
- Naval Air Warfare Center