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Rolling, yawing, and hinge moments produced by rectangular ailerons

Description: Ailerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
Date: January 1933
Creator: Heald, R. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet Propulsion with Special Reference to Thrust Augmenters

Description: An investigation of the possibility of using thrust augmented jets as prime movers was carried out. The augmentation was to be effected by allowing the jet to mix with the surrounding air in the presence of bodies which deflect the air set in motion by the jet. Six augmentation schemes were tested experimentally with compressed air at room temperature at jet speeds up to 1240 feet per second.
Date: January 1933
Creator: Schubauer, G. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Research Concerning Lateral Control Devices, Particularly at High Angles of Attack 7: Handley Page Tip and Full-Span Slots With Ailerons and Spoilers

Description: Tests were made with ordinary ailerons and different sizes of spoilers on rectangular Clark Y wing models with Handley Page tip and full span slots. The tests showed the effect of the control devices on the general performance of the wings as well as on the lateral control and lateral stability characteristics.
Date: January 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Working charts for the stress analysis of elliptic rings

Description: This report presents charts which reduce the stress analysis of circular and elliptic rings of uniform cross section subjected to balanced systems of concentrated loads from a statically indeterminate problem to a statically determinate one. To demonstrate the use of the charts in the stress analysis of elliptic rings, an illustrative problem is included.
Date: January 1933
Creator: Burke, Walter F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic Breaking Tests of Airplane Parts

Description: "The static stresses of airplane parts, the magnitude of which can be determined with the aid of static load assumptions, are mostly superposed by dynamic stresses, the magnitude of which has been but little explored. The object of the present investigation is to show how the strength of airplane parts can best be tested with respect to dynamic stresses with and without superposed static loading, and to what extent the dynamic strength of the parts depends on their structural design. Experiment… more
Date: January 1933
Creator: Hertel, Heinrich
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The D.V.L. Gliding-Angle Control (W. Hübner Design)

Description: This report describes a device for arbitrary enlargement of the gliding angle of airplanes, especially of such with flat gliding angle and difficult landing characteristics. The D.V.L. gliding angle control (design, Hubner) permits a local interruption of the lift distribution along the span and consequently an increased induced drag. The mechanism comprises two wing rudders operated by lever from the pilot's cockpit. Said rudders are fitted on the top side of the wing near the leading edge. Th… more
Date: January 1933
Creator: Hübner, Walter & Pleines, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Problem of the Propeller in Yaw With Special Reference to Airplane Stability

Description: The quantity of air which the disk area described by propeller blades travels through, is accelerated rearward conformably to the momentum of the forces acting on the propeller. The accelerated air mass forms behind the propeller the so-called slipstream, in which among others, the mean velocity of advance is increased. If the propeller axis slopes toward the relative flight direction, the slipstream direction likewise changes, i.e., it sets up a downwash behind the propeller.
Date: January 1933
Creator: Misztal, Franz
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Maneuverability investigation of an O3U-1 observation airplane

Description: From Summary: "This report presents the results of maneuverability tests of an O3U-1 observation airplane. This investigation is the third in a series of similar investigations requested by the Bureau of Aeronautics (Navy) for the purpose of comparing the maneuverability of different airplane types and to provide quantitative data for use in establishing a criterion or method for rating the maneuverability of an airplane. The two former investigations were conducted with the fighter types desig… more
Date: January 19, 1933
Creator: Thompson, F. L. & Kirschbaum, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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