Pressure-distribution measurements on a rectangular wing with a partial-span split flap in curved flight / by Frank G. Rokus.

Format:

Book

Government document

Author/Creator:

Rokus, Frank G., author.

Contributor:

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

Series:

Technical note (United States. National Advisory Committee for Aeronautics) ; 742.

Technical note / National Advisory Committee for Aeronautics ; No. 742

Language:

English

Subjects (All):

Aerodynamic load.

Flaps (Airplanes).

Split flaps (Airplanes).

Rolling (Aerodynamics).

Yawing (Aerodynamics).

Physical Description:

1 online resource (7 pages, 8 unnumbered pages) : illustrations.

Place of Publication:

Washington, [D.C.] : National Advisory Committee for Aeronautics, 1939.

Summary:

Pressure-distribution tests were made on the 32-foot whirling arm of the Daniel Guggenheim Airship Institute of a rectangular wing of N.A.C.A. 23012 section to determine the rolling and the yawing moment due to angular velcoity of yaw. The model was tested at 0 degrees and 5 degrees pitch; flaps 0 degrees, plus or minus 5 degrees, and plus or minus 10 degrees yaw; and with no flap and with split flaps at 25, 50, and 75 percent of the wing span and deflecte 60 degrees.

The results are given in the form of span load distributions and as calculated moment coefficients. The experimental values of rolling- and yawing-moment coefficients were in fairly close agreement with theory.

Notes:

Description based on online resource, title from title screen (viewed May 29, 2020).

"December 1939."

No Federal Depository Library Program (FDLP) item number.

Includes bibliographical references (page 6).

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

Other Format:

Print version: Rokus, Frank G. Pressure-distribution measurements on a rectangular wing with a partial-span split flap in curved flight

OCLC:

1156324008