Conceptual Design and Aerodynamic Analyses of a Generic UCAV Configuration

Liersch, Carsten M.; Huber, Kerstin Claudie

doi:10.2514/6.2014-2001

Cited by 37 publications

(26 citation statements)

References 11 publications

(10 reference statements)

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“…These operational points have been derived from typical missions used in DLR projects to assess the performance of military aircraft [69]. The onflow Mach number is M ∞ 0.4 and the operational assumed altitude is 4000 m. With these parameters, the flight Reynolds number is Re ∞ 52.6 × 10 6 , taking the chord length c ref 5 m as the reference length.…”

Section: Numerical Resultsmentioning

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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Section: Numerical Resultsmentioning

confidence: 99%

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

Schütte

2017

Journal of Aircraft

View full text Add to dashboard Cite

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“…These operational points have been derived from typical missions used in DLR projects to assess the performance of military aircraft. 69 The onflow Mach number is M ∞ = 0.4 and the operational assumed altitude is 4000m. With these parameters the flight Reynolds number is Re ∞ = 52.6·10 6 taking the chord length c ref = 5m as the reference length.…”

Section: Numerical Resultsmentioning

confidence: 99%

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

Schütte

Huber

Frink

et al. 2018

Journal of Aircraft

Self Cite

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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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“…Similar to the DLR design research on fixed-wing aircraft, presented by Liersch [13], the features of a distributed computation and a universal data model for harmonization and exchange are considered. Such modular and flexible workflows have shown to be very appropriate in civil and military fixed-wing design studies (see Liersch and Huber [14]), but are still not state of the art in rotorcraft design. This design methodology is the overall objective in the development of IRIS.…”

Section: Design Theorymentioning

confidence: 99%

Process Development for Integrated and Distributed Rotorcraft Design

2019

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The German Aerospace Center is currently developing a new design environment for rotorcraft, which combines sizing, simulation and evaluation tasks into one toolbox. The complete environment applies distributed computation on the servers of the various institutes involved. A uniform data model with a collaboration and interface software, developed by DLR and open source, are used for exchange and networking. The tools used apply blade element methods in connection with full six degrees of freedom trim, panel methods for aerodynamic loads, different empirical models for sizing, engine properties and component mass estimation and finite element methods for structural design. A special feature is the integration of a higher fidelity overall simulation tool directly into the sizing loop. The paper describes the use of the several tools for the phases of conceptual and preliminary design. A design study is presented demonstrating the sensitivity of the process for a variation of the input parameters exhibiting a broad range for trade-off studies. The possibility to continue for analyzing and sizing of the structural properties is also demonstrated by applying a finite element approach for specific load cases. These features highlight the core of the new design environment and enable the development of goal-oriented design processes for research especially of new and unconventional rotorcraft configurations. The work presented in this paper was conducted throughout the DLR internal project, namely the Technologies for Rotorcraft in Integrated and Advanced Design (TRIAD). TRIAD is a joint project of the institutes of Flight Systems, the institute of Aerodynamics and Flow Technology, the institute of Structures and Design, the System Architectures in Aeronautics and Institute of Aerospace Medicine and receives basic founding.

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Conceptual Design and Aerodynamic Analyses of a Generic UCAV Configuration

Cited by 37 publications

References 11 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

Process Development for Integrated and Distributed Rotorcraft Design

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