Pressure-distribution measurements on a tapered wing with a partial-span split flap in curved flight / by Th. Troller and F. Rokus.

Format:

Book

Government document

Author/Creator:

Troller, T., author.

Rokus, F., author.

Contributor:

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

Series:

Technical note (United States. National Advisory Committee for Aeronautics) ; 735.

Technical note / National Advisory Committee for Aeronautics ; No. 735

Language:

English

Subjects (All):

Aerodynamic load.

Airplanes--Wings--Testing.

Airplanes.

Flaps (Airplanes).

Split flaps (Airplanes).

Rolling (Aerodynamics).

Yawing (Aerodynamcics).

Physical Description:

1 online resource (6 pages, 6 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 tapered wing to determine the rolling and yawing moments due to an angular velocity in yaw. The model was tested at 0 degrees and 5 degrees pitch; 0 degrees, 5 degrees, and 10 degrees yaw; and with split flaps covering 25, 50, 75, and 100 percent of the wing span and deflected 60 degrees. The results are given in the form of 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, PDF version; title from title page (TRAIL, viewed December 6, 2021).

"November 1939."

No Federal Depository Library Program (FDLP) item number.

Includes bibliographical references (page 5).

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

Other Format:

Print version: Troller, T. Pressure-distribution measurements on a tapered wing with a partial-span split flap in curved flight

OCLC:

1156323833