K. Saitoh, R. Voss, H. Kheirandish

Details of unsteady aerodynamics for two dimensional wing of NLR-7301 with flap were numerically investigated by Navier-Stokes code in transonic regime. Unsteady aerodynamic coefficients such as lift and pitching moment show non-linear aspects in small amplitude range of forced excitation mode. Pressure distribution of super sonic region on upper surface is very sensitive to the incidence and this brings the nonlinearity of the unsteady aerodynamics in small amplitude range of pitching motion. Behavior of re-attachment of the boundary layer aft of shock wave also affects the nonlinearity. Shock wave motions were also examined. Linearized unsteady lift and pitching moment coefficients for each amplitude were applied to the eigen value analysis for the flutter boundary. Flutter simulations were also carried out and the results showed that the amplitude of the limit cycle oscillation could be explained by the flutter boundary of the eigen value analysis.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-10; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

transonic flows, unsteady aerodynamics, flutter

Bibliothek

2005