Flow control and high-lift performance for flying-wing manned Combat Air Vehicle Configurations by inserting lots

Ali, U; Chadwick, EA

Abstract

The objectives of the present study on Unmanned Combat Air Vehicles
(UCAVs) are two-fold: first to control the flow by inserting leading-edge and
cross-flow slots and analysing the viscous flow development over the outer
panels of a flying-wing configuration to maximise the performance of the
elevons control surfaces; second to predict high-lift performance particularly
the maximum-lift characteristics. This is demonstrated using a variety of
inviscid Vortex Lattice Method (VLM) and Euler, and viscous CFD Reynolds
Averaged Navier-Stokes (RANS) methods. The computational results are
validated against experiment measured in a wind tunnel. Two flying-wing
planforms are considered based around a generic 40 ̊ edge-aligned
configuration. The VLM predicts a linear variation of lift and pitching moment
with incidence angle, and substantially under-predicts the induced drag.
Results obtained from RANS and Euler agree well with experiment.

Citation

Ali, U., & Chadwick, E. (2016). Flow control and high-lift performance for flying-wing manned Combat Air Vehicle Configurations by inserting lots. International Journal of Multiphysics, 10(2), https://doi.org/10.21152/1750-9548.10.2.117

• Journal Article Type: Article
• Publication Date: Jun 30, 2016
• Deposit Date: Dec 13, 2016
• Publicly Available Date: Dec 13, 2016
• Journal: The International Journal of Multiphysics
• Print ISSN: 1750-9548
• Publisher: International Society of Multiphysics
• Volume: 10
• Issue: 2
• DOI: https://doi.org/10.21152/1750-9548.10.2.117
• Publisher URL: http://dx.doi.org/10.21152/1750-9548.10.2.117
• Related Public URLs: http://www.multi-science.co.uk/multiphysics.htm