J. Reneaux, A. Blanchard

Among the different techniques which could be applied to reduce the drag of transport aircraft, laminar flow technology seems to have the greatest potential. For high swept wings, laminar boundary layers can be stabilized by suction applied to the leading edge and by favourable pressure gradients in the spar box region. As an example of ONERA activities concerning this concept, this paper deals with the design of an airf oil with hybrid laminar flow control and describes the performance of a wing using this basic airfoil. The second pan of the paper is devoted to three tests carried out on this airfoil in the ONERA-CERT T2 cryogenic wind tunnel. Two models were devoted to the investigation of critical suction velocity in isolated holes and to the influence of different hole arrangements. Suction was applied to the third one between 7.5% and 27.5% of the chord to validate the streamwise transition prediction method.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.164-174; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, laminar flow, swept wings

Bestellbar

1992