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Results 15251 - 15260 of 17,147
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A load factor formula

A load factor formula

Date: August 1, 1927
Creator: Miller, Roy G
Description: The ultimate test of a load factor formula is experience. The chief advantages of a semi rational formula over arbitrary factors are that it fairs in between points of experience and it differentiates according to variables within a type. Structural failure of an airplane apparently safe according to the formula would call for a specific change in the formula. The best class of airplanes with which to check a load factor formula seems to be those which have experienced structural failure. Table I comprises a list of the airplanes which have experienced failure in flight traceable to the wing structure. The load factor by formula is observed to be greater than the designed strength in each case, without a single exception. Table II comprises the load factor by formula with the designed strength of a number of well-known service types. The formula indicates that by far the majority of these have ample structural strength. One case considered here in deriving a suitable formula is that of a heavy load carrier of large size and practically no reserve power.
Contributing Partner: UNT Libraries Government Documents Department
Wall interference in closed type wind tunnels

Wall interference in closed type wind tunnels

Date: March 1, 1927
Creator: Higgins, George J
Description: A series of tests has been conducted by the National Advisory Committee for Aeronautics, in the variable density wind tunnel on several airfoils of different sizes and sections to determine the effect of tunnel wall interference and to determine a correction which can be applied to reduce the error caused thereby. The use of several empirical corrections was attempted with little success. The Prandtl theoretical correction gives the best results and its use is recommended for correcting closed wind tunnel results to conditions of free air.
Contributing Partner: UNT Libraries Government Documents Department
Is there any available source of heat energy lighter than gasoline?

Is there any available source of heat energy lighter than gasoline?

Date: April 1, 1923
Creator: Meyer, P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The installation and correction of compasses in airplanes

The installation and correction of compasses in airplanes

Date: August 1, 1927
Creator: Schoeffel, M F
Description: The saving of time that results from flying across country on compass headings is beginning to be widely recognized. At the same time the general use of steel tube fuselages has made a knowledge of compass correction much more necessary than was the case when wooden fuselages were the rule. This paper has been prepared primarily for the benefit of the pilot who has never studied navigation and who does not desire to go into the subject more deeply than to be able to fly compass courses with confidence. It also contains material for the designer who wishes to install his compasses with the expectation that they may be accurately corrected.
Contributing Partner: UNT Libraries Government Documents Department
Extract from a report on the resistance of spheres of small diameter in an airstream of high velocity

Extract from a report on the resistance of spheres of small diameter in an airstream of high velocity

Date: March 1, 1921
Creator: Toussaint, & Hayer,
Description: Much attention is given here to the design of the wind tunnel and the experimental set-up. In comparing their results on the wind resistance of spheres to the results of other researchers, the authors find wide discrepancies. They are unable to explain the cause of the discrepancies, concluding, as they do, that the differing results could not be explained by the action of the wind tunnel walls.
Contributing Partner: UNT Libraries Government Documents Department
The dead weight of the airship and the number of passengers that can be carried

The dead weight of the airship and the number of passengers that can be carried

Date: January 1, 1922
Creator: CROCCO
Description: In order to determine an approximate formula giving the weight of a dead load as a function of the volume (V) of the envelope and of the maximum velocity (v), we will take the relative weight of the various parts of the airship (P(sub v), M, V, A, T(sup 34)), adopting a mean value of the coefficients determined. This formula may be adopted both for semi-rigid airships with suspended nacelle and non-rigid envelope, with or without internal suspensions. It may also be adapted to airships with rigid longitudinal beam, with power units on external supports or in nacelles, and with non-rigid envelopes, with or without internal bracing cables.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the N.A.C.A. control force recorder

Notes on the N.A.C.A. control force recorder

Date: July 1, 1923
Creator: Reeid, H J E
Description: Emphasized here is the desirability of using recording instruments in the investigation of the characteristics of airplanes with particular reference to the National Advisory Committee for Aeronautics (NACA) control force recorder. Given here are photographs, records, and a description of the instrument developed by NACA for investigations on different types of aircraft. Described here is an instrument for recording control forces. At present, this control force recorder registers only the forces exerted on the stick. However, attachments are being designed to enable the forces on the rudder bar also to be recorded. The instrument in its final form will consist of three parts, namely, the recorder, the controller for the stick, and the controller for the rudder. The first two are in use now. The theory of operation is simple. In the controller, which is slipped over and fastened to the stick, are small electrical resistances which vary with the force applied to the handle. The recording apparatus then consists of suitable variable resistances properly connected to galvanometers whose deflections are proportional to the forces applied to the stick.
Contributing Partner: UNT Libraries Government Documents Department
Absolute dimensions of Karman vortex motion

Absolute dimensions of Karman vortex motion

Date: January 1, 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theory of the ideal windmill

Theory of the ideal windmill

Date: July 1, 1921
Creator: Hoff, Wilhelm
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel

Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel

Date: January 1, 1923
Creator: Kutzbach, K
Description: The experimental flights described herein were made with the object of obtaining information regarding the following two questions, which as yet have not been sufficiently elucidated. These are: 1. What effect has altitude upon the formation of the mixture? 2. What alteration takes place, with increasing altitude, in the utilization of the heat contained in the fuel?.
Contributing Partner: UNT Libraries Government Documents Department