L. Gaudet, C.J. Betts, P.R. Ashill

This paper describes research concerned with identifying physical features of flows over a Natural Laminar Flow aerofoil, particularly where boundary-layer transition takes place. Measurements were made, using a well-established method for testing aerofoils, in the 8ft x 8ft Tunnel, RAE Bedford for Mach numbers in the region of 0.5 and for chord Reynolds numbers up to about 18 x 10^6. The measurement techniques used, including surface hot films, surface static pressures and total and static pressures in the wake, are described along with the procedures used to correct the data, for example, for tunnel-wall constraint. The surface hot films were used to make both unsteady and steady measurements, allowing both boundary-layer state and skin friction to be determined.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.132-140; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, boundary layer transition, laminar flow, wind tunnel

Bestellbar

1992