Effect of retractable-spoiler location on rolling- and yawing-moment coefficents / J.A. Shortal.

Format:

Book

Government document

Author/Creator:

Shortal, Joseph Adams, 1908- author.

Contributor:

United States. National Advisory Committee for Aeronautics, issuing body.

Series:

Technical note (United States. National Advisory Committee for Aeronautics) ; 499.

Technical note / National Advisory Committee for Aeronautics ; No. 499

Language:

English

Subjects (All):

Spoilers (Airplanes).

Flaps (Airplanes).

Airplanes--Control surfaces.

Airplanes.

Rolling (Aerodynamics).

Yawing (Aerodynamics).

Wind tunnel testing.

Physical Description:

1 online resource (12 pages, 5 unnumbered pages) : illustrations.

Place of Publication:

Washington, [D.C.] : National Advisory Committee for Aeronautics, 1934.

Summary:

In this report are presented the results of wind-tunnel tests of retractable spoilers on the upper surface of a Clark Y wing, which have been made as part of an investigation of lateral control devices being conducted. Spoilers with chords up to 15.0 percent of the wing chord were tested in several locations on a plain rectangular wing and in two locations on the same wing equipped with a 20.0 percent chord split flap down 60 degrees.

Notes:

Description based on online resource, title from title screen (viewed March 18, 2020).

"July 1934."

"Langley Memorial Aeronautical Laboratory."

No Federal Depository Library Program (FDLP) item number.

Includes bibliographical references (page 9)

Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.

Other Format:

Print version: Shortal, Joseph Adams, 1908- Effect of retractable-spoiler location on rolling- and yawing-moment coefficents

OCLC:

1145759772