H. Triebstein, J. Wagener

Experimental investigations on the steady and unsteady aerodynamic forces were performed on a wing / ejector engine model in the subsonic flow regime. The pressure measurements were made for the following parameters: velocity, angle of attack, mass flow, reduced frequency, and amplitude of oscillation of the engine performing pitch oscillations. For the wing/engine combination, the unsteady interference effects for engine oscillation on the pressure side of the wing are strongly affected by flow separation at the wing/pylon connection. The induced unsteady aerodynamic forces on the wing are small. The experimental results are ready to be compared with theories, which still must be developed for all necessary parameters. Problems with the test models, the test equipment, the measuring procedure, and the electronic data recording and processing are discussed.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.132-141; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991