H. Henke, U.R. Müller, B. Schulze

Progress in the development towards a new, time-accurate strong interaction method for computing unsteady transonic wing flow is reported. In the current version, an ADI-technique for solving the 3D unsteady Transonic Small Perturbation Equation has been extended by incorporating an unsteady 2D integral boundary layer method, and then simultaneously solving the viscous and inviscid flow equations in a stripwise f ashion. The strong-interaction technique is validated by comparison with experimental pressure distributions on a wing, which were recently measured in detail at various transonic Mach numbers. For steady and unsteady flows, the computed influence of viscous displacement on the pressure distribution is demonstrated in contrast to purely inviscid calculations. Given the elastic vibration modes for bending and torsion, the generalized aerodynamic forces are computed for several frequencies and Mach numbers, compared to those of other aeroelastic methods, and then applied to the computation of transonic flutter speeds.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.66-77; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991