This paper discusses the results of a cooperative experimental research program on a half-model of a fuselage and wing with high lift devices (slat and flap) equipped with zero and 25 deg sweep capability. Tests were made with two wing seeps, 0 and 25 deg. The results include: Basic forces and surface pressure distributions; Three-dimensional confluent boundary layer measurements at two spanwise and three chordwise stations on the main wing; Total pressure measurements at the slat cove; and Surface flow visualizations.
Effect of Wing Sweep on the Flow Around a Slat and Its Performance
1994
19 pages
Report
Keine Angabe
Englisch
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