A pseudo-compressibility method for solving inverse problems based on the 3D incompressible Euler equations

Ferlauto, Michele

doi:10.1080/17415977.2014.939653

Cited by 12 publications

(4 citation statements)

References 31 publications

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“…The aerodynamic design problem is reformulated here as an inverse problem [7,8] and coupled with an evolutionary optimizer based on Genetic Algorithms (GA) [9]. It is well known that GAs require a large number of iteration to converge.…”

Section: Mathematical Modelmentioning

confidence: 99%

“…The numerical solution is based on an OpenMP implementation of the shock-capturing Godunov method with Flux-Difference Splitting and second-order accurate Essentially Non-Oscillatory reconstruction scheme [12]. The URANS solver accuracy has been widely tested in many unsteady compressible flowfield involving stalled flows [13], moving grids [8], flow-instabilities [14].…”

Section: Flow Governing Equationsmentioning

confidence: 99%

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Optimal aerodynamic design of scramjet facility nozzles

Degregori¹,

Ferlauto²

2018

AIP Conference Proceedings

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An hybrid approach to optimization is applied to the aerodynamic design of a device that acts as a facility nozzle and inlet distortion generator for a direct-connect scramjet combustor test-rig. The solution of the design problem is sought by using different approaches of CFD analysis and optimization tools. The initial design is based on the solution of an inverse problem coupled to optimization by genetic algorithms. The result of the optimization is then tested by CFD simulations of the directconnect facility and the shock reflection patterns are compared toat of the in-flight configuration. The verification of nozzle design and the assessment of the prescribed flow distortion are then carried out by numerical simulations of the flowfield of the whole direct-connect facility by an URANS solver. The proposed procedure is checked by designing a facility nozzle and distortion generator system for a scramjet model available in the open literature.

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Section: Mathematical Modelmentioning

confidence: 99%

Section: Flow Governing Equationsmentioning

confidence: 99%

Optimal aerodynamic design of scramjet facility nozzles

Degregori¹,

Ferlauto²

2018

AIP Conference Proceedings

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“…The numerical method has been efficiently parallelized by using OpenMP directives. The spatial and time accuracy of the solver has been widely tested in many unsteady compressible flowfields as, for instance, the flow manipulation by synthetic jets and poststall control of NACA0015 profile [22]; the simulation of rotating stall generation and evolution [25]; time-dependent flows with moving grids [26,27]; and the computation of aeroelastic standard configurations and blade flutter. The computational domain is bounded by artificial (i.e., far-field) boundaries and physical contours (i.e., impermeable walls).…”

Section: Mathematical Modelmentioning

confidence: 99%

Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

Ferlauto

Marsilio

2017

AIAA Journal

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A computational method tailored for the simulation of fluidic thrust-vectoring systems is employed to investigate the dynamic response of a dual-throat nozzle in open-and closed-loop control. Thrust vectoring in fixed, symmetric nozzles is obtained by secondary flow injections that cause local flow separations, asymmetric pressure distributions, and, as a consequence, the vectoring of primary jet flow. The computational technique is based on a well-assessed mathematical model for the compressible unsteady Reynolds-averaged Navier-Stokes equations. A minimal control system governs the unsteady blowing. Nozzle performances and thrust-vector angles have been computed for a wide range of nozzle pressure ratios and secondary flow injection rates. The numerical results are compared with the experimental data available in the open literature. Several computations of the open-loop dynamics of the nozzle under different forcing have been performed to investigate the system response in terms of thrust-vectoring effectiveness and controllability. These computations have been used to extract autoregressive exogenous models of the nozzle dynamics. The effects of including the actuator dynamics are also discussed. Simple strategies of closed-loop control of the nozzle system by proportional-integrative-derivative regulators are investigated numerically. The closed-loop model predictive control of the system, based on the autoregressive exogenous models, is addressed.

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“…Methodology for the scalar Burger's equation was presented by Lellouche et al [38] in which the authors aimed to find the best approximation for the measured data by means of boundary control and an adjoint approach. Ferlauto [13] obtained optimal geometric shapes for aerodynamic bodies by solving an inverse problem for the three-dimensional incompressible Euler equations. Numerical computation of the optimization problems for conservation laws have been studied extensively due to the theoretical and numerical challenges that arise.…”

mentioning

confidence: 99%

Recovery of a Time-Dependent Bottom Topography Function from the Shallow Water Equations via an Adjoint Approach

Britton¹,

Chow²,

Chen³

et al. 2020

Preprint

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We develop an adjoint approach for recovering the topographical function included in the source term of one-dimensional hyperbolic balance laws. We focus on a specific system, namely the shallow water equations, in an effort to recover the riverbed topography. The novelty of this work is the ability to robustly recover the bottom topography using only noisy boundary data from one measurement event and the inclusion of two regularization terms in the iterative update scheme. The adjoint scheme is determined from a linearization of the forward system and is used to compute the gradient of a cost function. The bottom topography function is recovered through an iterative process given by a three-operator splitting method which allows the feasibility to include two regularization terms. Numerous numerical tests demonstrate the robustness of the method regardless of the choice of initial guess and in the presence of discontinuities in the solution of the forward problem.

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A pseudo-compressibility method for solving inverse problems based on the 3D incompressible Euler equations

Cited by 12 publications

References 31 publications

Optimal aerodynamic design of scramjet facility nozzles

Optimal aerodynamic design of scramjet facility nozzles

Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

Recovery of a Time-Dependent Bottom Topography Function from the Shallow Water Equations via an Adjoint Approach

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