By Topic

High-Fidelity Simulations for Maneuvering Unmanned Combat Air Vehicle Configurations

Sign In

Cookies must be enabled to login.After enabling cookies , please use refresh or reload or ctrl+f5 on the browser for the login options.

Formats Non-Member Member
$31 $13
Learn how you can qualify for the best price for this item!
Become an IEEE Member or Subscribe to
IEEE Xplore for exclusive pricing!
close button

puzzle piece

IEEE membership options for an individual and IEEE Xplore subscriptions for an organization offer the most affordable access to essential journal articles, conference papers, standards, eBooks, and eLearning courses.

Learn more about:

IEEE membership

IEEE Xplore subscriptions

3 Author(s)
Gordnier, R.E. ; Air Vehicles Directorate, US Air Force Res. Lab. ; Visbal, M.R. ; Sherer, S.E.

In this paper a high-order computational method for the highly unsteady, complex vortical flows over unmanned combat air vehicle (UCAV) like configurations is presented. A sixth-order compact difference scheme with an eighth-order low pass filter is used to solve the Navier-Stokes equations. An implicit large-eddy simulation (ILES) method which exploits the high-order accuracy of the compact difference scheme and uses the discriminating higher-order filter to regularize the flow is used to model the transition and turbulence in these highly separated flows. This computational approach is applied to the detailed characterization of the flowfield over a low sweep delta wing at moderate Reynolds numbers and both low and moderate freestream Mach numbers. Computations exploring the control of the vortical flows above a swept delta wing by use of a dialectric-barrier-discharge (DBD) actuator are also presented. With the actuator located near the apex, significant movement of the vortex breakdown location and a dramatic transformation of the shear-layer substructures are demonstrated

Published in:

HPCMP Users Group Conference, 2006

Date of Conference:

June 2006