Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0° to 20° at high subsonic speeds / by Bernard N. Daley and Douglas R. Lord.

Format:

Book

Government document

Author/Creator:

Daley, Bernard N., author.

Lord, Douglas R., author.

Contributor:

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

Series:

Technical note (United States. National Advisory Committee for Aeronautics) ; 3424.

Technical notes / National Advisory Committee for Aeronautics ; No. 3424

Language:

English

Subjects (All):

Aerofoils--Testing.

Aerofoils.

Angle of attack (Aerodynamics).

Physical Description:

1 online resource (57 pages) : illustrations

Other Title:

Aerodynamic characteristics of several six-percent-thick airfoils at angles of attack from zero degrees to twenty degrees at high subsonic speeds

Place of Publication:

Washington [D.C.] : National Advisory Committee for Aeronautics, 1955.

Summary:

Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types were conducted in the Langley rectangular high-speed tunnel. Static pressures along the surfaces of each airfoil were measured over a Mach number range from 0.3 to the choking Mach number (about 0.92 at alpha = 0 degrees) at angles of attack from 0 to 20 degrees. Total-pressure surveys in the wake were obtained for the same Mach number range at angles of attack from 0 to 8 degrees. Schlieren photographs of the air flow were also obtained for representative conditions.

The aerodynamic characteristics of each of the airfoils have been determined from the measured pressure data. These results showed that the lift-curve slope of each of the aerfoils decreased rapidly to a positive value approaching zero at angles of attack near 9 degrees and roughly maintained this value up to the highest angle of attack tested.

Notes:

Title from title screen (viewed March 7, 2019).

"May 1955."

"Langley Aeronautical Laboratory, Langley Field, Va."

"Supersedes recently declassified NACA RM L9E19. 1949"--Page 1

No Federal Depository Library Program (FDLP) item number.

Includes bibliographical references (page 10).

Print version record.

Other Format:

Paper version: Daley, Bernard N. Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds

OCLC:

1100474478