Accession Number:

ADA801379

Title:

Wind-Tunnel Investigation of a Tapered Wing with a Plug-Type Spoiler-Slot Aileron and Full-Span Slotted Flaps

Descriptive Note:

Wartime rept.

Corporate Author:

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY

Personal Author(s):

• Lowry, John G.
• Liddell, Robert B.

Report Date:

1942-07-01

Pagination or Media Count:

31.0

Abstract:

An investigation was made in the 7- by 10-foot wind tunnel of the Langley Memorial Aeronautical Laboratory of several arrangements of a plug-type spoiler-slot aileron on a tapered wing model of a typical fighter airplane having a full-span slotted flap. The plug-type aileron is essentially a tapered plug that fits into a slot through the wing to conform to the original external wing contour when in the neutral position. When the aileron is deflected, the plug projects from the upper surface of the wing as a spoiler and, at the same time, makes a slot through the wing behind the spoiler. The static rolling-, yawing-, and hinge-moment coefficients were determined and are presented for several angles of attack and flap deflections. Estimates of the rolling effectiveness and the stick forces for a fighter airplane are also given. The results indicate that a plug-type spoiler-slot aileron will provide satisfactory lateral control on tapered-wing airplanes with full-span slotted flaps. Pivoting the top plate of the plug and providing a simple linkage for deflecting the plate relative to the plug offers a powerful means of adjusting stick forces.

Descriptors:

• *SLOTTED FLAPS
• *FLAPS(CONTROL SURFACES)
• *AILERONS
• MOMENTS
• ANGLE OF ATTACK
• WIND TUNNEL TESTS
• WINGS
• LINKAGES
• AERONAUTICAL LABORATORIES
• SPOILERS
• HINGES
• DEFLECTION
• ROLL
• FIGHTER AIRCRAFT
• POSITION(LOCATION)

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE