Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

Schütte, Andreas; Einarsson, Gunnar; Raichle, Axel; Schöning, Britta; Orlt, Matthias; Neumann, Jens; Arnold, Johannes; Mönnich, W.; Forkert, T.

doi:10.2514/1.31182

Cited by 64 publications

(13 citation statements)

References 18 publications

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“…The experimental results are documented by Rein et al [18]. The numerical results using TAU are described in detail in Schütte et al [19][20][21][22][23]. Additional results are given by Boelens [24] and Jirasek and Cummings [25].…”

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

Schütte

2017

Journal of Aircraft

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“…The vehicle is a supermaneuverable fighter that was built by the United States and West Germany in the 1990s. The test aircraft has been a subject of extensive flight, and wind-tunnel tests (see for example Canter and Groves [78], Alcorn et al [79], Williams et al [80], and Rein et al [81]) and CFD simulations (an example is the work of Schütte et al [5]). A three-view drawing of the vehicle is shown in Fig.…”

Section: Test Casementioning

confidence: 99%

“…Unfortunately, this makes the solution of the aircraft equations of motion an infinite-dimensional problem, where the current states depend on the evolution of previous states at infinitely many points in time [4]. With advances in computing techniques, one straightforward way to solve this problem is to develop a full-order model based on direct solution of discretized Reynolds-averaged Navier-Stokes (RANS) equations coupled with the dynamic equations governing the aircraft motion [5][6][7].…”

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Transonic Aerodynamic Load Modeling of X-31 Aircraft Pitching Motions

Ghoreyshi¹,

Cummings²,

Ronch³

et al. 2013

AIAA Journal

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The generation of reduced-order models for computing the unsteady and nonlinear aerodynamic loads on an aircraft from pitching motions in the transonic speed range is described. The models considered are based on Duhamel's superposition integral using indicial (step) response functions, Volterra theory using nonlinear kernels, radial basis functions, and a surrogate-based recurrence framework, both using time-history simulations of a training maneuver(s). Results are reported for the X-31 configuration with a sharp leading-edge cranked delta wing geometry, including canard/wing vortex interactions. The validity of the various models studied was assessed by comparison of the model outputs with time-accurate computational-fluid-dynamics simulations of new maneuvers. Overall, the reduced-order models were found to produce accurate results, although a nonlinear model based on indicial functions yielded the best accuracy among all models. This model, along with a time-dependent surrogate approach, helped to produce accurate predictions for a wide range of motions in the transonic speed range. = regression coefficients ε = kriging random process μ = air viscosity; kriging mean value ρ = density, kg∕m 3 σ 2 = covariance τ ij = viscous stress tensor components, Pa Φ i X = radial basis functions ω = circular frequency, rad∕s

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“…Growth in computing capacity and the development of numerical techniques has recently led to significant progress in finding solutions for Navier-Stokes equations coupled with the dynamics equations governing the aircraft motion, facilitating flight dynamics studies [3,[5][6][7][8][9][10]. However, at present the problems of fluid mechanics and flight dynamics cannot be solved simultaneously in certain flight mechanical applications-for example, in semi-realistic simulation of the aircraft flight using ground-based flight simulators or control system design [3,11].…”

Section: Introductionmentioning

confidence: 99%

Experimental Study and Neural Network Modeling of Aerodynamic Characteristics of Canard Aircraft at High Angles of Attack

Ignatyev

Храбров

2018

Aerospace

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Flow over an aircraft at high angles of attack is characterized by a combination of separated and vortical flows that interact with each other and with the airframe. As a result, there is a set of phenomena negatively affecting the aircraft's performance, stability and control, namely, degradation of lifting force, nonlinear variation of pitching moment, positive damping, etc. Wind tunnel study of aerodynamic characteristics of a prospective transonic aircraft, which is in a canard configuration, is discussed in the paper. A three-stage experimental campaign was undertaken. In the first stage, a steady aerodynamic experiment was conducted. The influence of a reduced oscillation frequency and angle of attack on unsteady aerodynamic characteristics was studied in the second stage. In the third stage, forced large-amplitude oscillation tests were carried out for the detailed investigation of the unsteady aerodynamics in the extended flight envelope. The experimental results demonstrate the strongly nonlinear behavior of the aerodynamic characteristics because of canard vortex effects on the wing. The obtained data are used to design and test mathematical models of unsteady aerodynamics via different popular approaches, namely the Neural Network (NN) technique and the phenomenological state space modeling technique. Different NN architectures, namely feed-forward and recurrent, are considered and compared. Thorough analysis of the performance of the models revealed that the Recurrent Neural Network (RNN) is a universal approximation tool for modeling of dynamic processes with high generalization abilities.

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Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

Abstract: Red-flap grid Blue-back ground cut out box Blue-rigid Red-elastic

Cited by 64 publications

References 18 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

Transonic Aerodynamic Load Modeling of X-31 Aircraft Pitching Motions

Experimental Study and Neural Network Modeling of Aerodynamic Characteristics of Canard Aircraft at High Angles of Attack

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