UCAV model design and static experimental investigations to estimate control device effectiveness and S&amp;C capabilities

Huber, Kerstin Claudie; Vicroy, Dan D.; Schuette, Andreas; Huebner, Andreas

doi:10.2514/6.2014-2002

Cited by 43 publications

(25 citation statements)

References 13 publications

(18 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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].…”

mentioning

confidence: 85%

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

Schütte

2017

Journal of Aircraft

View full text Add to dashboard Cite

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

show abstract

mentioning

confidence: 85%

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

Schütte

2017

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…A 7th axis push rod enables a larger range of motion than would be possible with only the standard pitch link. Further details of the experimental set-up can be found in Huber et al 15 Along with the baseline configuration that is essentially the same as the SACCON model, the DLR-F19 model includes trailing edge control surfaces. The control surfaces are designated by the side of the model on which they are located, as well as whether or not they are located inboard or outboard, as seen in Figure 3.…”

Section: Background and Simulation Proceduresmentioning

confidence: 99%

Static and Dynamic Simulations of a Generic UCAV Geometry Using the Kestrel Flow Solver

Lofthouse

Ghoreyshi

Jirasek

et al. 2014

32nd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

The Kestrel CFD solver is used to characterize the static and dynamic aerodynamic behavior of a generic UCAV configuration with control surfaces, named the DLR-F19. Computational results are compared to wind tunnel data from experiments performed in DNW-NWB wind tunnel at several different angles-of-attack, ranging from 0 to 30 degrees, with no flap deflections and flap deflections for maximum roll. Results for several angles-ofsideslip are also presented. The aerodynamics around the UCAV configuration are highly nonlinear, even at moderate angles-of-attack, due to vortex interactions. In general, good agreement between computational results and the wind tunnel experimental data for total force coefficients is achieved using relatively inexpensive steady-state simulations with the SARC turbulence model for the static cases, and unsteady simulations with the SARC turbulence model for the dynamic pitching motions. However, unsteady simulations using a DDES turbulence model are required for angels-of-attack greater than 20-degrees. The computational models have difficulty predicting the finer details of the nonlinear moments, most likely due to the challenge of accurately predicting separation and vortex breakdown. This work is a contribution to the NATO RTO Task Group AVT-201 on Stability and Control estimation methods.

show abstract

“…Finally, within the AVT-201 the SACCON with control surfaces has been explored. 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.…”

Section: A Backgroundmentioning

confidence: 93%

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

Schütte

Huber

Frink

et al. 2018

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

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

UCAV model design and static experimental investigations to estimate control device effectiveness and S&C capabilities

Cited by 43 publications

References 13 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

Static and Dynamic Simulations of a Generic UCAV Geometry Using the Kestrel Flow Solver

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

Contact Info

Product

Resources

About