APPLICATION OF FLOW CONTROL TO A DISC-WING UAV

UAVSystems.pdf (877Kb)

Jonathan R. Potts & William J. Crowther
Aerospace Group, School of Mechanical, Aerospace and Civil Engineering, University of Manchester, UK

Abstract
A spin stabilised axi-symmetric disc-wing has potential application as a highly manoeuvrable, unpowered unmanned air vehicle or guided projectile. This paper considers the means by which aerodynamic control moments can be generated on such a disc-wing. The present experimental investigation outlines the aerodynamics of a non-spinning axi-symmetric disc-wing with and without forced transition strips installed on the disc rim. Fences fixed normal to the surface and the local flow direction provide promising control moments of useful magnitude. It is proposed that the control moments produced by passive transition strips or flow obstructing fences on a non-rotating disc-wing are achievable by a similar active flow control method such as active turbulent strips or on-demand fences. A simple analysis of disc-wing flight manoeuvres predicts the turning radius and time period of a 90 degree banked turn based on experimental data.

Reference in Full
Potts J.R. & Crowther W.J.: Application of Flow Control to a Disc-wing UAV, 16th Bristol UAV Systems Conference, Bristol, UK, April 2001.