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Stability and control assessment of a generic UCAV design using the edge flow solver
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2014 (English)In: 32nd AIAA Applied Aerodynamics Conference, 2014Conference paper (Refereed)
Abstract [en]

Accurate estimations of control effectiveness are crucial for flight mechanical model development to assess controllability. Any deficiency in the design should be corrected at an early stage. An increased interest in Unmanned Combat Aerial Vehicles (UCAV) has put focus on the controllability of low observable platforms with highly sweep delta wings without the traditional fin. The NATO STO task group AVT-201 was formed to meet this stability and control challenge and build on previous knowledge gained on complex vortical flow of rounded leading-edge delta wings. This paper presents the numerical results, using the FOI developed flow solver Edge, of the common cases for the DLR-F19 model. The effect of trailing-edge ap deections was investigated using steady RANS or time-accurate hybrid RANS-LES methods. Both static and dynamic pitch cases at low speed and high angle of attack were evaluated and compared to experimental data.

Place, publisher, year, edition, pages
Keyword [en]
Aerodynamics, CFD, SACCON, UCAV, Computational fluid dynamics, Delta wing aircraft, Flow simulation, Military vehicles, Navier Stokes equations, Accurate estimation, Control effectiveness, High angle of attack, Hybrid rans-les methods, Stability and control, Unmanned combat aerial vehicles, Flight control systems
National Category
Fluid Mechanics and Acoustics
URN: urn:nbn:se:kth:diva-167852ScopusID: 2-s2.0-84903887589ISBN: 9781624102882OAI: diva2:821267
32nd AIAA Applied Aerodynamics Conference 2014, 16 June 2014 through 20 June 2014, Atlanta, GA

QC 20150615

Available from: 2015-06-15 Created: 2015-05-22 Last updated: 2015-06-15Bibliographically approved

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Tomac, MaximilianRizzi, Arthur
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