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 Collection: Technical Report Archive and Image Library
Tests and approximate analysis of bending stresses due to torsion in a D-section box

Tests and approximate analysis of bending stresses due to torsion in a D-section box

Date: May 1, 1944
Creator: Brilmyer, Harold G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests at Mach number 1.62 of a series of missile configurations having tandem cruciform lifting surfaces

Tests at Mach number 1.62 of a series of missile configurations having tandem cruciform lifting surfaces

Date: January 11, 1952
Creator: Grigsby, Carl E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests for determining the effect of a rotating cylinder fitted into the leading edge of an airplane wing

Tests for determining the effect of a rotating cylinder fitted into the leading edge of an airplane wing

Date: March 1, 1926
Creator: Wolff, E B & Koning, C
Description: Experiments were performed with a wing model, to which a rotary cylinder had been fitted. The rotation of the cylinder had a remarkable effect on the aerodynamic properties of the wing.
Contributing Partner: UNT Libraries Government Documents Department
Tests for the determination of the stress condition in tension fields

Tests for the determination of the stress condition in tension fields

Date: November 1, 1936
Creator: Lahde, R & Wagner, H
Description: The present experiments treat the stress of actual tension fields within the elastic range. They give the magnitude of the flexural stresses due to wrinkling. They also disclose, particularly by slightly exceeded buckling load, the marked unloading - as compared with the tension-field theory - of the uprights as a result of the flexural stiffness of the web plate. The test sheets were clamped at the edges and brought to buckling through shearing and compressive stresses applied in the direction of the long sides.
Contributing Partner: UNT Libraries Government Documents Department
Tests for the elimination of tail flutter

Tests for the elimination of tail flutter

Date: June 1, 1933
Creator: Biechteler, Curt
Description: On various low-wing monoplanes the horizontal tail surfaces flutter in flight at large angles of attack and occasionally in curvilinear flight. This flutter leads to torsional vibrations of the rear end of the fuselage, as manifested by vibrations of the control stick. According to the earlier DVL investigations tail flutter is due to the influence, on horizontal tail surfaces, of eddies or vortices shed at large angles of attack by the upper surface of the wing root. The cause of tail flutter on a low-wing monoplane and the means of preventing it are investigated in the present report.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank

Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank

Date: October 1, 1942
Creator: Ashworth, C Dixon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail

Date: June 25, 1953
Creator: Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics

Date: February 11, 1952
Creator: Graham, David & Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail  : longitudinal characteristics

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : longitudinal characteristics

Date: April 23, 1951
Creator: Graham, David & Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail : longitudinal and lateral characteristics

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail : longitudinal and lateral characteristics

Date: April 13, 1953
Creator: Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department