Stability and control assessment of a generic UCAV design using the edge flow solver

• 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.

Ämnesord

TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Strömningsmekanik och akustik (hsv//swe)

ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Fluid Mechanics and Acoustics (hsv//eng)

Nyckelord

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

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