A. Karl, K.A. Bütefisch, J. Reichmuth, H.-R. Höfer

The aim of this study was to provide experimental flow field data on a delta wing for comparison with theoretical results of different numerical codes. For this purpose in addition to force and pressure distribution measurements velocity measurements by means of a three component laser Doppler anemometer were performed in the 1 x 1 m^2 transonic wind tunnel (TWG) of the DFVLR. The 420 mm chord model of HHB was tested at a Mach number of M_ = 0.85 and angles of attack of alpha = 10°, 20°, and 24°. The Reynolds number based on model chord was Re= 4.5 x 10^6. Flow visualization by laser sheet technique was used to get in addition a first insight in the structure of the whole flow field and quantitative data of the positions of the vortices.

5. DGLR-Fach-Symposium Arbeitsgemeinschaft Strömungen mit Ablösung, München, 1986

Conference Paper

englisch

14,8 x 21,0 cm, 18 Seiten

DGLR-Bericht, 1986, 1986-03, Strömungen mit Ablösung; S.285-302; 1986; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics

Bestellbar

1986