Numerical Simulation of Control Surface Deflections over a Generic UCAV configuration at Off-design Flow Conditions

Kennett, David; Hoholis, George; Badcock, K. J.

doi:10.2514/6.2014-2134

Cited by 12 publications

(4 citation statements)

References 9 publications

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“…The results of the very comprehensive windtunnel investigations over a wide range of onflow conditions are documented by Huber et al [39], Vicroy et al [40] and Rein et al [41] the numerical work is ea. published by Frink [42], Hitzel and Zimper [43], Kennett et al [44], Lofthouse et al [45] and Jirasek et al [46]. The TAU results are summarized by the author in Schütte et al [47].…”

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confidence: 98%

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Schütte

2017

Journal of Aircraft

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The present work is investigating the vortex-dominated flow physics as well as the aerodynamic behavior of swept wing configurations with round leading edges. The research is based on numerical simulations using the computational fluid dynamics method DLR TAU. The target configurations are swept wings of constant aspect ratio, variable leading-edge contours, and leading-edge sweep angles. The work deals with the onset of the vortical flow at the leading edge for constant and variable leading-edge nose radii, the influence of the angle of attack, the leading-edge sweep, and the onflow Mach number. Furthermore, the aerodynamic behavior is analyzed and assessed, as well as the specific flow physics in the vicinity of the vortical flow separation at round leading edges. The objective of the present work is to provide a contribution for the design and assessment of the physical characteristics of swept wing configurations. Furthermore, sensitivities will be given for the design process. In addition, the current investigation provides a deeper understanding of the separation onset process and the flow physics of swept wing configurations with round leading edges. Nomenclaturewing reference length, depth of the wing, m M ∞ = onflow Mach number, equal to a∕U ∞ p = pressure, N∕m 2 q ∞ = onflow dynamic pressure, N∕m 2 Re ∞ = Reynolds number, equal to U ∞ · c ref ∕ν r = radius at nose of the profile, m r N = nondimensional leading-edge contour radius, equal to r∕c ref s = wing semispan, m T = temperature, K t = time, s U ∞ = onflow velocity, m∕s u = local velocity within the flowfield, m∕s x, y, z = Cartesian coordinates, m y W = initial wall distance, distance of first grid point from wing surface, m y = nondimensional value to assess resolution of boundary-layer wall unit, equal to τ W ∕ρ p · y W ∕ν α = angle of attack, deg β = angle of sideslip, deg γ = circulation Δt = discrete time step, s Δx = discrete step in space, m μ = dynamic viscosity, Ns∕m 2 ν = kinematic viscosity, m 2 ∕s ρ = density, kg∕m 3 τ W = wall friction, N∕m 2 φ = wing sweep, deg k∂ρ∕∂tk = density residual, kg∕m 3 s Subscripts le = leading edge r = root ref = reference parameter ∞ = onflow condition

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confidence: 98%

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Schütte

2017

Journal of Aircraft

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“…The angles of attack (α) are taken as 0°, 5°, 10°, 15°, and 20°, respectively. The comparison of the force coefficients between the CFD and the experiment 13 is shown in Figure 5. Except for the stall case of α = 20°, the CFD results at other angles of attack are in good agreement with the experimental values.…”

Section: Models and Numerical Methodsmentioning

confidence: 99%

Research on the roll control of the flapless aircraft with circulation control

Wang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The purpose of this paper is to study the roll control of the flapless aircraft under low-speed and high-speed flight states and investigate the equivalent control effect (ECE) and the power consumption of the pneumatic control. First, the roll moment coefficient of the aircraft with different aileron deflection angles is calculated. Then the intensity of the jet is adjusted to match the roll moment coefficient, so that the deflection angle of the ailerons and the intensity of the jet corresponding to the same rolling moment are found. Based on the realization of the roll control, the aerodynamic efficiency of the flapless aircraft is evaluated by using the equivalent lift-to-drag ratio ( Ecc) considering power consumption. The ECE curves of the pneumatic roll control under low-speed and high-speed flight states are obtained. Under low-speed flight state, the increment of aerodynamic efficiency brought by the jet cannot make up for its power consumption. Under high-speed flight state, the aerodynamic efficiency increment brought by the pneumatic control can compensate its power consumption before Cl = 0.061.

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“…The results of the very comprehensive wind tunnel investigations over a wide range of onflow conditions are documented by Huber et al, 38 Vicroy et al 39 and Rein et al 40 the numerical work is ea. published by Frink, 41 Hitzel and Zimper, 42 Kennett et al, 43 Lofthouse et al 44 and Jirasek et al 45 The TAU results are summarized by the author in Schütte et al 46 Within the German technology program SAGITTA (Latin for Arrow) experimental an numerical investigations have been conducted on a 53 • diamond wing configuration with a variable leading edge contour. By Hövelmann and Breitsamter 47 leading-edge geometry effects have been evaluated on the diamond wing by examining the effect of various combinations of round and sharp contour areas along the leading edge.…”

Section: A Backgroundmentioning

confidence: 99%

Stability and Control Investigations of Generic 53 Degree Swept Wing with Control Surfaces

Schütte

Huber

Frink

et al. 2018

Journal of Aircraft

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The present work is investigating the vortex dominated flow physics as well as the aerodynamic behavior of swept wing configurations with round leading edges. The research is based on numerical simulations using the CFD method DLR TAU. The target configurations are swept wings of constant aspect ratio, variable leading edge contours and leading edge sweep angles. The work is dealing with the onset of the vortical flow at the leading edge for constant and variable leading edge nose radii, the influence of the angle of attack, the leading edge sweep and the onflow Mach number. Furthermore, the aerodynamic behavior is analyzed and assessed as well as the specific flow physics in the vicinity of the vortical flow separation at round leading edges. The objective of the present work is to provide a contribution for the design and assessment of the physical characteristics of swept wing configurations. Furthermore, sensitivities will be given for the design process. In addition, the current investigations provide a deeper understanding of the separation onset process and the flow physics of swept wing configurations with round leading edges.

show abstract

Numerical Simulation of Control Surface Deflections over a Generic UCAV configuration at Off-design Flow Conditions

Cited by 12 publications

References 9 publications

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Research on the roll control of the flapless aircraft with circulation control

Stability and Control Investigations of Generic 53 Degree Swept Wing with Control Surfaces

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