Small Disturbance Euler Equations: Efficient and Accurate Tool for Unsteady Load Prediction

Kreiselmaier, Erich; Laschka, Boris

doi:10.2514/2.2699

Cited by 56 publications

(31 citation statements)

References 7 publications

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“…In this study, the solver AER-Eu is employed which uses an Euler set of equations discretized on structured, collocated ¦nite-volume grids [4]. The strongly conservative form guarantees shock-capturing without any additional e¨ort.…”

Section: Methodsmentioning

confidence: 99%

Influencing the aerodynamics of the ACFA2020 aircraft with flap and trailing edge device oscillations

Meyer

Breitsamter

2013

Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics

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The in §uence of an oscillating aileron and trailing edge device on the unsteady aerodynamics of a blended wing body (BWB) aircraft con¦guration with high-¦delity time-accurate Euler simulations has been investigated. Steady results show an unequally-distributed lift distribution in spanwise direction with a particularly severe shock at cruise conditions on the outboard wing. Unsteady oscillations of the outboardlocated aileron are able to in §uence the local and global aerodynamics. The oscillation of the trailing edge device designed to be at trailing edge of the aileron does not show any great e¨ect on neither local nor global aerodynamics.

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Section: Methodsmentioning

confidence: 99%

Influencing the aerodynamics of the ACFA2020 aircraft with flap and trailing edge device oscillations

Meyer

Breitsamter

2013

Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics

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“…These methods are especially suitable for simulations at low reduced frequencies. Recently, numerical methods based on such an alternative approach, namely on the solution to small disturbance Euler equations (SDE) and the linearization of NavierStokes equations, have been presented [7] and [8].…”

Section: Fig 1 Transonic Dipmentioning

confidence: 99%

Boundary Layer Method for Unsteady Transonic Flow

Majić¹,

Voß²,

Virag³

2012

SV-JME

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“…This approach avoids an overdetermined in-/outflow constraint, giving the far-field boundary a degree of nonreflectivity [18]. As the already established FLM-methods (FLM-NS, FLM-SDEu, and the underlying dynamically fully nonlinear Euler method FLM-Eu [12]) all have been realized in the Fortran 90 programming language, it was continuously employed to implement the extension toward FLM-SD.NS.…”

Section: Methodsmentioning

confidence: 99%

“…It had been realized as the viscous extension of the already well established small disturbance Euler method FLM-SDEu [12]. The two-dimensional incarnation of FLM-SD.NS for high-Reynolds-number flow was originally presented in [13], where a detailed derivation of the underlying governing equations and a synopsis of the general properties is given.…”

Section: Methodsmentioning

confidence: 99%

Small Disturbance Navier-Stokes Computations for Low-Aspect-Ratio Wing Pitching Oscillations

Pechloff

Laschka

2010

Journal of Aircraft

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For dynamic production aeroelastic analysis in the transonic speed range, a computational fluid dynamics method based on the small disturbance Navier-Stokes equations can serve as a reasonable alternative to one realizing the Reynolds-averaged Navier-Stokes equations' time-domain solution. Its dynamically linear approach promises a significantly decreased computation cost in the prediction of unsteady aerodynamic loading while retaining the latter's fidelity to a high degree. In this regard, research conducted at the Technical University of Munich has resulted in the computational fluid dynamics method FLM-SD.NS. Further substantiating its application readiness, harmonic pitching oscillations of the NASA clipped delta wing are investigated. Test cases are characterized by shocks of varying strengths and ranges of motion, as well as leading-edge vortex formation. Overall, results are in good agreement with dynamically fully nonlinear solutions provided by the comparative Reynolds-averaged NavierStokes solver FLM-NS, as well as available experimental data. Reductions in computation time, up to an order of magnitude, in relation to FLM-NS are observed. Limitations of the small disturbance approach, however, become apparent for the leading-edge vortex case, in which higher-order harmonics are far less negligible in the flow's response to the excitation.

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Small Disturbance Euler Equations: Efficient and Accurate Tool for Unsteady Load Prediction

Cited by 56 publications

References 7 publications

Influencing the aerodynamics of the ACFA2020 aircraft with flap and trailing edge device oscillations

Influencing the aerodynamics of the ACFA2020 aircraft with flap and trailing edge device oscillations

Boundary Layer Method for Unsteady Transonic Flow

Small Disturbance Navier-Stokes Computations for Low-Aspect-Ratio Wing Pitching Oscillations

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