U. Dreßler, H. Hansen, S. Rill, K.-H. Horstmann, C.-H. Rohardt, G. Wichmann

In a combined effort of DA Bremen and DLR Braunschweig a partspan, full chord natural laminar flow wing glove was designed for the Fokker FlOO test aircraft. The design point at a Machnumber of M = 0.75, a lift coefficient of cL = 0.40 combined with a Reynoldsnumber of Re = 22.O x l0^6 and a leading edge sweep of [phi]LE = 20° reflects typical cruise conditions of future European regional aircraft. During the design process the main emphasis had to be put on the integration of the laminar type of pressure distribution of the glove into the FlOO wing. To counteract the influences of the basic wing special fairing airfoils were designed while the glove itself consists of three different generator airfoils.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.152-163; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, boundary layer transition, laminar flow, fokker f100 aircraft

Bestellbar

1992