D.I.A. Poll, M. Danks, A.J. Davies

An experimental investigation has been conducted into the problem of boundary-layer transition in the immediate vicinity of a swept leading-edge. The geometry and associated Reynolds numbers are such that the tests are effectively super flight scale. Of specific interest are the issues of attachment-line contamination and cross-flow instability since these are known to be "barrier" problems in the design of swept, laminar-flow wings. Boundary-layer suction is provided by means of laser drilled holes in a titanium surface. Preliminary results indicate that, without suction, and with an uncontaminated attachmentline flow, transition occurs through cross-flow instability. When suction is used, cross-flow transition can be effectively delayed by very low through surface velocities. Comparisons are made between the impervious surface data and the predictions of the linear stability theory e^9 model for transition. The agreement is found to be good for the attachment-line flow but poor for cross-flow.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.278-283; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

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

Bestellbar

1992