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Technical Report Archive and Image Library
Wind-Tunnel Investigations on a Changed Mustang Profile with Nose Flap Force and Pressure-Distribution Measurements
Date: September 1, 1947
Creator: Krueger, W.
Description: Measurements are described which were taken in the large wind tunnel of the AVA on a rectangular wing "Mustang 2" with nose flap of a chord of 10 percent. Besides force measurements the results of pressure-distribution measurements are given and compared with those on the same profile "without" nose flap.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64848/
Wind-tunnel investigations on flexural-torsional wing flutter
Date: September 1, 1938
Creator: Voigt, H
Description: For the purpose of testing the theory of an oscillating airfoil of two degrees of freedom, a wing was mounted in the wind tunnel between two walls in such a manner that it could execute vertical (flexural) oscillations as well as torsional oscillations about an arbitrary axis parallel to the span. It was possible to vary the inertia and elasticity parameters and also to increase artificially the negligibly small natural damping of the system. The oscillations were recorded to a strongly magnified scale. The experimentally determined critical (or flutter) velocities fully agree with the theoretical ones of Wagner and Kussner within the limits of computational and measuring accuracy. An extremely narrow wing without end walls (three dimensional problem) showed the same oscillations as one with end walls (two-dimensional problem).
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63293/
Wind-tunnel measurement of static forces on internally carried bombs of two different bluff shapes in the flow field of a swept-wing fighter-bomber configuration at a Mach number of 1.6
Date: April 1, 1957
Creator: Geier, D. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53156/
Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail
Date: April 25, 1955
Creator: Beam, B. H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53200/
Wind-tunnel measurements of air loads on split flaps
Date: May 1, 1934
Creator: Wenzinger, Carl J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54562/
Wind-tunnel measurements of the dynamic cross derivative (rolling moment due to yawing velocity and to acceleration in sideslip) of the Douglas D-558-II airplane and its components at supersonic speeds including description of the technique
Date: November 3, 1955
Creator: Boatright, William B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62122/
Wind-tunnel measurements of wing buffeting on 1/16-scale model of Douglas D-558-II research airplane
Date: September 24, 1956
Creator: Kemp, William B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62868/
Wind-Tunnel Measurements on the Henschel Missile "Zitterrochen" in Subsonic and Supersonic Velocities
Date: April 1, 1948
Creator: Weber
Description: At the request of the Henschel Aircraft Works. A. G. Berlin. three models of the missile "Zitterrochen" were investigated at subsonic velocities.(open jet 215-millimeter diameter) and at supersonic velocities (open jet 110 by 130 millimeters) in order to determine the effect of various wing forms on the air forces and moments. Three-component measurements were taken, and one model was also investigated with deflected control plates.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63980/
Wind Tunnel of the Bucharest Polytechnic Institute
Date: December 1, 1931
Creator: unknown
Description: This report describes the Bucharest wind tunnel and presents numerous photographs and diagrams. The wind tunnel is of the closed- circuit type, the return being symmetrical with respect t o the longitudinal axis of the tunnel. Th e tunnel is of the horizontal type with a diameter of 3. 2 m (10. 5-ft.) a t the beginning of the entrance cone, and 1.5 m ( 4,92 ft.) at the entrance to the test chamber. The latter, 2 m (6.56 ft.) long, may be either of the open-jet type or enclosed in a cylindrical housing.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63607/
Wind-tunnel of three lateral-control devices in combination with a full-span slotted flap on an NACA 23012 airfoil
Date: August 1, 1938
Creator: Wenzinger, Carl J
Description: A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section, and two-dimensional flow was approximated. The model was fitted with a full-span slotted flap having a chord 25.66 percent of the airfoil chord. The ailerons investigated extended over the entire span and each had a chord 10 percent of the airfoil chord. The types of ailerons tested were: retractable ailerons, slot-lip ailerons using the lip of the slot for ailerons, and plain ailerons on the trailing edge of the slotted flap. The data are presented in the form of curves of section lift, drag, and pitching-moment coefficients for the airfoil with flap deflected but with ailerons neutral, and of rolling-moment, yawing-moment, and hinge-moment coefficients calculated for a rectangular wing of aspect ratio 6 with a semi-span aileron and a full-span flap. For the ailerons investigated the data indicate that, from considerations of rolling and yawing moments produced and of stick forces desired, the retractable aileron is the most satisfactory means of lateral control for use with a full-span slotted flap.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54435/