X. Zhang, A. Rona, G.M. Lilley

Near-field flow oscillations and the far-field noise radiation of a supersonic flow over a cavity of length to depth ratio L / D = 3 at Mach numbers 1.5 and 2.5 have been studied. The method employed a coupled scheme of computational fluid dynamics and aeroacoustics. The unsteady flow has been analysed by solving the Reynolds-averaged N avier-Stokes equations. Turbulence was modelled using a two-equation k-w model including compressibility corrections. A Godunov-type solver has beeri used to enhance the shock resolution. The flow field computational analysis provided source terms in a coupled far-field noise estimation scheme based on Lighthills acoustic analogy. The effects of the boundary were estimated using Curies modification to Lighthill equation, extended by Ffowcs Williams and Hawkings to include convective amplification. The near-field flow prediction has been compared with an earlier experiment and good agreement was achieved. The far-field noise calculation established the dominant noise source generation regions and the dominant direction of the oscillations.

First Joint CEAS/AIAA Aeroacoustics Conference, München, 1995

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 1995, 1995-01, First Joint CEAS/AIAA Aeroacoustics Conference - Proceedings; S.285-292; 1995; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1995