High speed static experimental investigations to estimate control device effectiveness and S&amp;C capabilities

Rein, Martin; Irving, Jonathan; Rigby, Glyn; Birch, Trevor

doi:10.2514/6.2014-2004

Cited by 32 publications

(11 citation statements)

References 1 publication

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: 86%

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: 86%

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

“…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

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

“…Reynolds numbers were adjusted via the total pressure to match those of preceding tests in which forces and moments were determined (Re = 2.1·10 6 -2.8·10 6 ). 13 Main topic of the present experimental tests has been providing information on the flow topology on the lee side of the configuration. For this purpose surface oil flow images have been produced.…”

Section: B Transonic Wind Tunnel Dnw-twgmentioning

confidence: 99%

Experimental and numerical analysis of the transonic vortical flow over a generic lambda wing configuration

Zimper

Rein

2014

32nd AIAA Applied Aerodynamics Conference

Self Cite

View full text Add to dashboard Cite

Transonic flows over the generic lambda wing configuration SACCON are considered for Mach numbers in the range 0.5 ≤ M ∞ ≤ 0.8. These flows are governed by an interaction of compressibility effects and vortical flows. In order to analyze the related flow physics, experimental and numerical approaches are combined. In wind tunnel tests, performed in the transonic tunnel DNW-TWG, the SACCON configuration was tested at a reduced scale of 1:20.5 at Reynolds numbers 2.1·10 6 ≤ Re ≤ 2.8·10 6 . Surface oil flow visualizations provide information on separation and reattachment lines, and thus also on vortex systems on the lee side of the model. In addition, schlieren images showing vortex structures and shock waves provide a first impression of the three-dimensional flow field. Detailed information on threedimensional flow fields have been obtained from numerical simulations carried out with the DLR TAU-Code. CFD results obtained with different turbulence models have been validated by comparison with skin friction lines of surface oil flow visualizations. Based on CFD results it is shown that at higher Mach numbers the presence of supersonic flow regimes limits the propagation of information and in this manner strongly influences vortex flows on the wing. Furthermore, at high angles of attack the particular design of the SACCON configuration results in strong shock-vortex interactions. These features lead to complex flow phenomena that can affect flight characteristics of the SACCON configuration over the entire flight envelope. Nomenclature 1 AVT Executive Officer, DLR Program Coordination Defence and Security Research @ NATO/STO Collaboration Support Office (CSO), BP 25, , Member AIAA.α = angle of attack [] μ = dynamic viscosity [kg / (s m)] ρ = density [kg m -3 ] C P = (p-p ∞ )/(0.5·ρ ∞ ·V ∞ 2 ), pressure coefficient [-] C P * = critical pressure coefficient, corresponding to a local Mach number of 1.0 [-] l µ = mean aerodynamic chord M ∞ = free-stream Mach number [-] M = local Mach number [-] p = static pressure [Pa] p ∞ = free-stream static pressure [Pa] Re = ρ·V ∞ ·l µ /μ, Reynolds number [-] V ∞ = free-stream velocity [m s -1 ] x = chordwise coordinate [m] y = spanwise coordinate [m] y + = dimensionless wall distance [-] z = vertical coordinate [m] AVT = Applied Vehicle Technology DLR = German Aerospace Center (Deutsches Zentrum für Luft-und Raumfahrt e.V.) Downloaded by UNIVERSITY OF TENNESSEE on October 1, 2015 | http://arc.aiaa.org |

show abstract

High speed static experimental investigations to estimate control device effectiveness and S&C capabilities

Cited by 32 publications

References 1 publication

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

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

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

Experimental and numerical analysis of the transonic vortical flow over a generic lambda wing configuration

Contact Info

Product

Resources

About