G. Schrauf, H. Bieler, P. Thiede

Transition prediction is a key problem of laminar flow technology. The design of transonic NLF and HLF wings requires efficient numerical methods to predict laminar-turbulent boundary layer transition on swept wings. In the present paper, an overview of transition prediction tools developed recently at Deutsche Airbus is given. We discuss the eN -method based on linear stability theory of incompressible and compressible boundary layers with and without curvature as it is used at Deutsche Airbus. Furthermore, we present the influence of pressure gradient, sweep angle, compressibility, as well as curvature on computed N-factors and outline the calibration procedure using the ATTAS flight tests and large-scale wind tunnel experiments in the DNW and the ONERA Sl.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.73-82; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, boundary layer transition, laminar flow, turbulent flow, swept wings

Bestellbar

1992