T. Mauermann

In this paper a new residual unsteady aerodynamic model suitable for the simulation of maneuvering aircraft is presented. Rather than obtaining the time domain unsteady aerodynamic loading from a rational function approximation of frequency domain loads, the model is based on accurate steady aerodynamic loads from a database in combination with a time stepping lifting-surface method. The time stepping method provides circulatory load correction factors for the steady database loads and unsteady non-circulatory load increments. It is based on a solution by vortex rings and allows for the accurate modelling of the wake shape. As a test case, a typical modern transport aircraft wing is analyzed. Steady calculations performed with the lifting-surface method are in excellent agreement with a commercial vortex lattice method. The effect of wing thickness is quantified by comparison with surface panel and Euler CFD computations. Unsteady calculations performed with the lifting-surface method are compared to an analytical approximation for a finite aspect ratio wing in heaving motion and show good agreement. The residual unsteady aerodynamic model is tested for the heaving motion of the transport aircraft wing and compared to unsteady Euler CFD reference results. The new method shows good agreement for total wing lift and pitching moment but over-predicts the unsteady effect for local lift and pitching moment.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 22 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-22; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

simulation, time domain analysis, unsteady aerodynamics

Bibliothek

2005