A.M. Rampurawala, K.J. Badcock

This paper describes a buzz simulation performed on a Japanese Supersonic Transport (SST) configuration. The SST wing profiles are characterised by a small wing thickness optimised for operation in supersonic cruise conditions. Due to the thinness of the wing there is limited space for constraints of the control surfaces at the trailing edge making them susceptible to a buzz instability in transonic conditions. In the current work an FEM structural model is constructed and analysed for natural modes and frequencies using NASTRAN. A flap is attached to the wing with a spring attachment and its oscillation controlled by adjusting the spring stiffness. 3D buzz simulation is performed using the Glasgow University multiblock CFD code PMB. Characteristics of buzz first noticed in experiments and 2D simulations are observed. Two types of flap treatment for CFD based calculations are used to simulate buzz and the results compared. Effect of buzz on the flutter boundary is also investigated and compared with flutter results obtained from NASTRAN. The wing bending and torsion frequencies are similar to the those obtained from a GVT test and the flap mode is included to see the effect it has on the flutter speed.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 23 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-23; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

aeroelasticity, control surfaces

Bibliothek

2005