Computationally efficient simulation of unsteady aerodynamics using POD on the fly. (7th November 2016)

• Record Type: Journal Article
• Authors: Moreno-Ramos, Ruben; Vega, José M; Varas, Fernando
• Is Part Of: Fluid dynamics research. Volume 48:Number 6(2016:Dec.)
• Publication Date: 2016-11-07
• Subjects: aeroelasticity -- unsteady aerodynamics -- transonic flow -- shock waves -- reduced order model -- POD on the fly; Fluid dynamics -- Periodicals; 620.106
• DOI: 10.1088/0169-5983/48/6/061424
• Languages: English
• ISSNs: 0169-5983

Abstract

Abstract: Modern industrial aircraft design requires a large amount of sufficiently accurate aerodynamic and aeroelastic simulations. Current computational fluid dynamics (CFD) solvers with aeroelastic capabilities, such as the NASA URANS unstructured solver FUN3D, require very large computational resources. Since a very large amount of simulation is necessary, the CFD cost is just unaffordable in an industrial production environment and must be significantly reduced. Thus, a more inexpensive, yet sufficiently precise solver is strongly needed. An opportunity to approach this goal could follow some recent results (Terragni and Vega 2014 SIAM J. Appl. Dyn. Syst. 13 330–65 ; Rapun et al 2015 Int. J. Numer. Meth. Eng. 104 844–68 ) on an adaptive reduced order model that combines 'on the fly' a standard numerical solver (to compute some representative snapshots), proper orthogonal decomposition (POD) (to extract modes from the snapshots), Galerkin projection (onto the set of POD modes), and several additional ingredients such as projecting the equations using a limited amount of points and fairly generic mode libraries. When applied to the complex Ginzburg–Landau equation, the method produces acceleration factors (comparing with standard numerical solvers) of the order of 20 and 300 in one and two space dimensions, respectively. Unfortunately, the extension of the method to unsteady, compressible flows around deformable geometries requires new approaches to deal with deformable meshes, high-Reynolds numbers, and compressibility. A first step in this direction is presented considering the unsteady compressible, two-dimensional flow around an oscillating airfoil using a CFD solver in a rigidly moving mesh. POD on the Fly gives results whose accuracy is comparable to that of the CFD solver used to compute the snapshots.