P.C. Chen

Recent development in the applications of the overset field-panel method to various wing with/without control surfaces are described. Our objective is to validate the overset field-panel method, also known as the ZTRAN method, with available measured data and the unsteady Computational-Fluid Dynamics (CFD) codes, which include CFL3D, ENS3DAE, and CAPTSD. In all cases studied, it is found that the ZTRAN results agree well with the CFD results and the experimental data. For wings with control surfaces, unlike the CFD methods which require an extensive grid generation effort to model the flap motion, modeling effort for flap motion for ZTRAN is minimum and is the same as that of the linear panel methods such as doublet lattice method and ZONA6. The Aerodynamic Influence Coefficient matrix generated by ZTRAN can be repeatedly used in a structural design loop. It is believed that the ZTRAN method with the present validation effort will be upheld as an integral part of matured technology for transonic aeroelastic applications.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 13 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-13; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

aeroelasticity, computational fluid dynamics, control surfaces, wings

Bibliothek

2005