English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Tools annual

Global: Zendy Free Plan

Global: Zendy Tools monthly

Global: Zendy Plus monthly

Experimental studies on a delta slab lifting body and a thin delta wing at high angles of attack are conducted in the supersonic wind tunnel and hypersonic gun tunnel, respectively. The schlieren pictures and the oil flow patterns in supersonic tests reveal that intermittent breakdown of the leeward vortices causes a chaotic temporal variation of the normal force with large amplitude in a narrow range of the freestream Mach number and angle of attack. Such unsteadiness can be eliminated by controlling the arrangement of the vortices with the use of bent nose and body flaps. The electric discharge method is applied to visualize low density leeward flow in hypersonic tests. The relation between the luminescence pattern and the flow structure is discussed.

Visualization of Wake Flows over High-Angles-of-Attack Delta Configurations at Supersonic and Hypersonic Speeds