K.-H. Horstmann, S.J. Miley

Hotwire anemometer measurements have been carried out in laminar flow on the wing of an aircraft in flight and on the same wing in the German Dutch Windtunnel (DNW). Beside the data of the traversable hotwire probes detailed chordwise pressure distribution data and indications of transition locations by the infrared image technique have been taken. For both test environments Tollmien-Schlichting (TS) waves are easily identifiable. Additional externally induced disturbances are visible which can lead to specific TS wave development. In the flight case propeller disturbances and in the windtunnel case a higher level of low f requency noise are identifiable. Nevertheless comparisons of measured transition with calculated amplification ratios show no difference between flight and wind tunnel tests.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.45-51; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, laminar flow

Bestellbar

1992