Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Huber, Kerstin Claudie; Schütte, Andreas; Rein, Martin

doi:10.2514/6.2012-3325

Cited by 22 publications

(16 citation statements)

References 7 publications

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“…The investigations applying the CFD solver TAU are published by Schütte et al [35]. Results for compressible and transonic onflow conditions are given in publications from Huber et al [36], Zimper and Rein [37] as well as Zimper and Hummel [38]. The achievements of the AVT-161 task group are the detailed analysis and understanding of the complex flow physics around the SACCON and the effects on the overall aerodynamics as well as the stability and control behavior.…”

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confidence: 99%

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: 99%

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

Schütte

2017

Journal of Aircraft

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“…26 Additional results of flow field measurements can be found in Konrath et al 27 and Gilliot. 28 The numerical results and analysis of the flow physics of the SACCON are documented in several publications by Frink, 29 Vallespin et al, 30 Tormalm and Schmidt, 31 Le Roy and Morgand 32 as well as Cummings et al 33 The investigations applying the CFD solver TAU are published by the author in Schütte et al 34 Results for compressible and transonic onflow conditions are given in publications from Huber et al, 35 Zimper and Rein 36 as well as Zimper and Hummel 37 . The achievements of the AVT-161 Task Group are the detailed analysis and understanding of the complex flow physics around the SACCON and the effects on the overall aerodynamics as well as the stability and control behavior.…”

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.

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“…8 First experimental and numerical investigations with the SACCON configuration, mostly in the subsonic regime, have been carried out within the NATO STO Task group AVT-161 "Assessment of Stability and Control Prediction Methods for NATO Air & Sea Vehicles" and within an internal DLR project. 2,3,4,9,10,11,12 …”

Section: Introductionmentioning

confidence: 99%

“…This configuration is characterized by a leading edge whose geometry varies in spanwise direction. Several experimental and numerical investigations have already been conducted within the subsonic speed range with a wind tunnel model that has been downscaled by 1:8 with respect to the original configuration 2,3,4 . However, most of the time real configurations operate at transonic velocities.…”

Section: Introductionmentioning

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

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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 |

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Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Cited by 22 publications

References 7 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

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

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