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NACA Stall-Warning Indicator

NACA Stall-Warning Indicator

Date: October 1, 1938
Creator: Thopmson, F L
Description: The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region. Thin drop in total pressure caused the contraction of a pressure cell to which the total-head tube and the static orifice are connected and closed an electrical circuit that actuates a warning signal.
Contributing Partner: UNT Libraries Government Documents Department
Operational treatment of the nonuniform-lift theory in airplane dynamics

Operational treatment of the nonuniform-lift theory in airplane dynamics

Date: October 1, 1938
Creator: Jones, Robert T
Description: The method of operators is used in the application of nonuniform-lift theory to problems of airplane dynamics. The method is adapted to the determination of the lift under prescribed conditions of motion or to the determination of the motions with prescribed disturbing forces.
Contributing Partner: UNT Libraries Government Documents Department
Static longitudinal stability and longitudinal control of autogiro rotors

Static longitudinal stability and longitudinal control of autogiro rotors

Date: October 1, 1938
Creator: Schrenk, M
Description: The present report discusses three different systems of elevator control and their effects on the stability and maneuverability of autogiros: (a) ailerons and elevators (standard); (b) blade control (la Cierval); (c) gravity control (new).
Contributing Partner: UNT Libraries Government Documents Department
The twisting of thin-walled, stiffened circular cylinders

The twisting of thin-walled, stiffened circular cylinders

Date: October 1, 1938
Creator: Schapitz, E
Description: On the basis of the present investigation of the twisting of thin-walled, stiffened cylinders the following conclusions can be reached: 1) there is as yet no generally applicable formula for the buckling moment of the skin; 2) the mathematical treatment of the condition of the shell after buckling of the skin is based on the tension-field theory, wherein the strain condition is considered homogenous.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Air Inlet and Outlet Openings for Aircraft, Special Report

Wind-Tunnel Investigation of Air Inlet and Outlet Openings for Aircraft, Special Report

Date: October 1, 1938
Creator: Rogallo, Francis M. & Gauvain, William E.
Description: An investigation was made in the NACA 5-foot vertical wind tunnel of a large variety of duct inlets and outlets to obtain information relative to their design for the cooling or the ventilation systems on aircraft. Most of the tests were of openings in a flat plate but, in order to determine the best locations and the effects of interference, a few tests were made of openings in an airfoil. The best inlet location for a system not including a blower was found to be at the forward stagnation point; for one including a blower, the best location was found to be in the region of lowest total head, probably in the boundary layer near the trailing edge. Design recommendations are given, and it is shown that correct design demands a knowledge of the external flow and of the internal requirements in addition to that obtained from the results of the wind tunnel tests.
Contributing Partner: UNT Libraries Government Documents Department
The effects of partial-span plain flaps on the aerodynamic characteristics of a rectangular and a tapered Clark Y wing

The effects of partial-span plain flaps on the aerodynamic characteristics of a rectangular and a tapered Clark Y wing

Date: September 1, 1938
Creator: House, R O
Description: An investigation was made to determine the aerodynamic characteristics of tapered and rectangular wings with partial-span plain flaps. Two Clark Y airfoils equipped with center section and with tip-section flaps were tested. The results showed that the aerodynamic characteristics of partial-span plain flaps were, in general, similar to those of split flaps of the same span, but that the lift and the drag were less for the wing with plain flaps than for the wing with split flaps of comparable size. For the rectangular wing with center-section plain flaps, the maximum lift and the lift-drag ratio at maximum lift were greater and the drag at maximum lift was less than for the wing with tip-section plain flaps of the same size. The maximum lift of the tapered wing varied in the same manner as that of the rectangular wing but the drag and the lift-drag-ratio relationship were opposite.
Contributing Partner: UNT Libraries Government Documents Department
Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails III : mass distributed along the wings

Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails III : mass distributed along the wings

Date: September 1, 1938
Creator: Seidman, Oscar & NEIHOUSE A I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Gyroscopic instruments for instrument flying

Gyroscopic instruments for instrument flying

Date: September 1, 1938
Creator: Brombacher, W G & Trent, W C
Description: The gyroscopic instruments commonly used in instrument flying in the United States are the turn indicator, the directional gyro, the gyromagnetic compass, the gyroscopic horizon, and the automatic pilot. These instruments are described. Performance data and the method of testing in the laboratory are given for the turn indicator, the directional gyro, and the gyroscopic horizon. Apparatus for driving the instruments is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Heat-stressed structural components in combustion-engine design

Heat-stressed structural components in combustion-engine design

Date: September 1, 1938
Creator: Kraemer, Otto
Description: Heated structural parts alter their shape. Anything which hinders free heat expansion will give rise to heat stresses. Design rules are thus obtained for the heated walls themselves as well as for the adjoining parts. An important guiding principle is that of designing the heat-conducting walls as thin as possible.
Contributing Partner: UNT Libraries Government Documents Department
Investigations on the downwash behind a tapered wing with fuselage and propeller

Investigations on the downwash behind a tapered wing with fuselage and propeller

Date: September 1, 1938
Creator: Muttray, H
Description: The new downwash measurements behind a tapered wing with parallel center section described in the present report can be brought into good agreement with theoretical calculations if made on the basis of not-rolled-up vortex sheet and allowance is made for the lowering of the sheet. The test values are about 1 degree higher than the "upper limit" established for it, as against approximately 0.5 degrees in the earlier tests behind a rectangular and elliptical wing. The measurements on lateral axes, especially if lying below the wing on a level with the vortex train, disclosed in accord with the lift distribution, a marked change in angle over the span of the tail in contrast to the rectangular and elliptical wing.
Contributing Partner: UNT Libraries Government Documents Department