Fuselage stress analysis

Fuselage stress analysis

Date: January 1, 1920
Creator: Warner, Edward P & Miller, Roy G
Description: Report analyzes the stresses in a fuselage of the built-up type in which the shear is taken by diagonal bracing wires. Tests are conducted for landing, flying, and thrust loads.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel balances

Wind tunnel balances

Date: January 1, 1920
Creator: Warner, Edward P & Norton, F H
Description: Report embodies a description of the balance designed and constructed for the use of the National Advisory Committee for Aeronautics at Langley Field, and also deals with the theory of sensitivity of balances and with the errors to which wind tunnel balances of various types are subject.
Contributing Partner: UNT Libraries Government Documents Department
Slip-stream corrections performance computation

Slip-stream corrections performance computation

Date: January 1, 1920
Creator: Warner, Edward P
Description: This report is an analysis of experiments performed by Eiffel on the air velocity in slip stream of a propeller, and also includes a theoretical discussion of the magnitude of the velocity in different propellers.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary report on free flight tests

Preliminary report on free flight tests

Date: January 1, 1920
Creator: Warner, E P & Norton, F H
Description: Results are presented for a series of tests made by the Advisory Committee's staff at Langley Field during the summer of 1919 with the objectives of determining the characteristics of airplanes in flight and the extent to which the actual characteristics differ from those predicted from tests on models in the wind tunnel, and of studying the balance of the machines and the forces which must be applied to the controls in order to maintain longitudinal equilibrium.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic properties of thick aerofoils suitable for internal bracing

The aerodynamic properties of thick aerofoils suitable for internal bracing

Date: January 1, 1920
Creator: Norton, F H
Description: The object of this investigation was to determine the characteristics of various types of wings having sufficient depth to entirely inclose the wing bracing, and also to provide data for the further design of such sections. This type of wing is of interest because it eliminates the resistance of the interplane bracing, a portion of the airplane that sometimes absorbs one-quarter of the total power required to fly, and because these wings may be made to give a very high maximum lift. Results of the investigation of the following subjects are given: (1) effect of changing the upper and lower camber of thick aerofoils of uniform section; (2) effect of thickening the center and thinning the tips of a thin aerofoil; (3) effect of adding a convex lower surface to a tapered section; (4) effect of changing the mean thickness with constant center and tip sections; and (5) effect of varying the chord along the span.
Contributing Partner: UNT Libraries Government Documents Department
Construction of models for tests in wind tunnels

Construction of models for tests in wind tunnels

Date: January 1, 1920
Creator: Norton, F H
Description: Report deals with the methods of constructing aerofoils and all other parts of a model airplane, including discussion of the degree of accuracy.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of wing truss stresses including the effect of redundancies

Analysis of wing truss stresses including the effect of redundancies

Date: January 1, 1921
Creator: Warner, E P & Miller, R G
Description: Airplane wing trusses are generally designed to contain redundant members (stagger wires and external drag wires) which, according to common practice, are not taken into account in calculations, so as to simplify the stress analysis by rendering the structure statically determinate. A more accurate method, in which the redundancies are included, involves a solution by means of Castigliano's method of least work. For the purpose of demonstrating the practical application of the method of least work this report presents examples for stresses of several cases of loading worked out for a structure similar to that of the Curtiss JN-4h. Case 1 was taken as the condition of velocity of 100 miles per hour combined with the angle of attack of maximum lift. Case 1a assumed the same loading but neglected the distortion of wooden members in the least-work analysis. So little error was involved in case 1a that this simplified method was employed for each succeeding case. Case 2 assumed a diving speed of 120 miles per hour and an angle of attack of no lift. Case 3 was worked out for the conditions imposed by the sand load recommended in NACA technical note no. 6.
Contributing Partner: UNT Libraries Government Documents Department
The efficiency of small bearings in instruments of the type used in aircraft

The efficiency of small bearings in instruments of the type used in aircraft

Date: January 1, 1921
Creator: Norton, F H
Description: This report deals with the construction and properties of bearings and pivots for use in instruments. The static and running friction for both thrust and radial loads was determined for a number of conical pivots and cylindrical and ball bearings. The static rocking friction was also measured for several conical and ball bearings under a heavy load, especially to determine their suitability for use in N. P. L. (National Physical Laboratory) type wind tunnel balance. In constructing conical pivots and sockets it was found that the pivots should be hardened and highly polished, preferably with a revolving lap, and that the sockets should be made by punching with a hardened and polished punch. It was found that for a light load the conical pivots give less friction than any other type, and their wearing qualities when hardened are excellent. Very small ball bearings are unsatisfactory because the proportional accuracy of the balls and races is not high enough to insure smooth running. For rocking pivots under heavy loads it was found that a ball-and-socket bearing, consisting of a hemispherical socket and a sphere of smaller diameter concentric with it, with a row of small balls resting between the two, was ...
Contributing Partner: UNT Libraries Government Documents Department
The Design of Wind Tunnels and Wind Tunnel Propellers

The Design of Wind Tunnels and Wind Tunnel Propellers

Date: January 1, 1919
Creator: Warner, Edward P; Norton, F H & Hebbert, C M
Description: Report discusses the theory of energy losses in wind tunnels, the application of the Drzewiecki theory of propeller design to wind tunnel propellers, and the efficiency and steadiness of flow in model tunnels of various types.
Contributing Partner: UNT Libraries Government Documents Department
Airplane Stress Analysis

Airplane Stress Analysis

Date: January 1, 1918
Creator: Zahm, A F & Crook, L H
Description: Report presents stress analysis of individual components of an airplane. Normal and abnormal loads, sudden loads, simple stresses, indirect simple stresses, resultant unit stress, repetitive and equivalent stress, maximum steady load and stress are considered.
Contributing Partner: UNT Libraries Government Documents Department
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