Unsteady Transonic Airfoil Flow Simulations using High-Order WENO Schemes

I. Klioutchnikov (), J. Ballmann (), H. Oliver, V. Hermes and A. Alshabu
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I. Klioutchnikov: RWTH Aachen University, Shock Wave Laboratory
J. Ballmann: RWTH Aachen University, Mechanics Department Lehr- und Forschungsgebiet für Mechanik
H. Oliver: RWTH Aachen University, Shock Wave Laboratory
V. Hermes: RWTH Aachen University, Shock Wave Laboratory
A. Alshabu: RWTH Aachen University, Shock Wave Laboratory

A chapter in Hyperbolic Problems: Theory, Numerics, Applications, 2008, pp 617-624 from Springer

Abstract: The flow over a supercritical airfoil in the transonic regime contains a lot of complex physical phenomena and interactions. High demands are made on the numerical model for an accurate numerical investigation of such a flow type. High-order (N ≥ 5) WENO (Weighted Essentially Nonoscillatory) schemes are appropriate for the numerical simulation of transonic flows, as they have the capability to capture shocks, resolve vortices, and predict their interactions. A high-order finite difference WENO scheme is applied to simulate the unsteady flow over the supercritical BAC3-11 [1] airfoil. The numerical results are compared with experiments carried out in a transonic shock tube and found in good agreement with the experimental data. The influences of Ma and Re number are studied.

Keywords: Mach Number; Vortical Structure; WENO Scheme; Normalize Power Spectrum; Supersonic Region (search for similar items in EconPapers)
Date: 2008
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-540-75712-2_61

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DOI: 10.1007/978-3-540-75712-2_61

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