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UNT Libraries Government Documents Department
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English
Serial/Series Title:
NACA Technical Reports
Collection:
Technical Report Archive and Image Library
Fuselage stress analysis
Date: January 1, 1920
Creator: Warner, Edward P
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65725/
Wind tunnel balances
Date: January 1, 1920
Creator: Warner, Edward P
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65722/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65721/
The Limiting Velocity in Falling from a Great Height
Date: January 1, 1919
Creator: Wilson, Edwin Bidwell
Description: The purpose of this report is to give a simple treatment of the problem of calculating the final or limiting velocity of an object falling in vertical motion under gravity in a resisting medium. The equations of motion are easily set up and integrated when the density of the medium is constant and the resistance varies as the square of the velocity. The results show that the fundamental characteristics of the vertical motion under gravity in a resisting medium is the approach to a terminal or limiting velocity, whether the initial downward velocity is less or greater than the limiting velocity. This method can be used to calculate the terminal velocity of a bomb trajectory.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65727/
Preliminary report on free flight tests
Date: January 1, 1920
Creator: Warner, E P
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65720/
Bomb trajectories
Date: January 1, 1920
Creator: Wilson, Edwin Bidwell
Description: The report is a mathematical treatise dealing with the trajectories of bombs of high terminal velocity, dropped from a great altitude.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65728/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65724/
Comparison of United States and British standard pitot tubes
Date: January 1, 1920
Creator: Zahm, A F
Description: The results shown in this report give a comprehensive comparison of the accuracy of United States and British standard pitot tubes.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65729/
The Parker variable camber wing
Date: January 1, 1920
Creator: Parker, H F
Description: This report deals with the problem of increasing the speed range of an airplane by varying the camber of a wing surface. The variable camber wing offers many advantages over the variable incidence type of speed range.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65726/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc65723/