P.C. Steimle, W. Schröder, W. Limberg, W. Althaus

Wind tunnel tests with force and pressure measurements have been performed using an oscillating rigid swept wing to investigate unsteady aerodynamic phenomena in the context of non-linear flow behavior and the development of aeroelastic instabilities in the transonic flight regime. The interaction of the flow field with an oscillating wing structure is studied on the basis of forced rotary oscillations with different amplitudes and frequencies. The wing oscillates about a mean angle of incidence of 0° at Mach numbers between 0.5 and 0.92 corresponding to Reynolds numbers of 0.97 to 2.0 million. The wing model has a supercritical BAC 3-11/RES/30/21 airfoil geometry with a relative thickness of 11%, a leading edge sweep back angle of 34° and an aspect ratio of 10.3. Unsteady transonic flow phenomena are analyzed on the basis of steady pressure distributions and flow visualization with the liquid crystal technique. The results show a damping effect of the coexisting trailing-edge and shock induced separation and an amplification of pressure fluctuations in the area of the shock-boundary layer interaction.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-12; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

unsteady aerodynamics

Bibliothek

2005