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 Collection: Technical Report Archive and Image Library
Results 15391 - 15400 of 17,329
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Velocity Distribution in the Boundary Layer of a Submerged Plate

Velocity Distribution in the Boundary Layer of a Submerged Plate

Date: October 1, 1930
Creator: Hansen, M
Description: This report deals with the measurement of the velocity distribution of the air in the velocity of a plate placed parallel to the air flow. The measurements took place in a small wind tunnel where the diameter of the entrance cone is 30 cm and the length of the free jet between the entrance and exit cones is about 2.5 m. The measurements were made in the free jet where the static pressure was constant, which was essential for the method of measurement used.
Contributing Partner: UNT Libraries Government Documents Department
Westland "Wessex" commercial airplane (British) : a high-wing semicantilever monoplane

Westland "Wessex" commercial airplane (British) : a high-wing semicantilever monoplane

Date: October 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Alterations and tests of the "Farnboro" engine indicator

Alterations and tests of the "Farnboro" engine indicator

Date: September 1, 1930
Creator: Collins, John H , Jr
Description: The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of putting pressure lines on the record. The modified indicator gives a complete record of the average cyclic variation in pressure per crank degree for any set of engine operating conditions which can be held constant for the period of time required to build up the composite card. The value of the record for accurate quantitative measurement is still questioned, although the maximum indicated pressure recorded on the motoring and power cards checks the readings of the balanced diaphragm type of maximum cylinder pressure indicator.
Contributing Partner: UNT Libraries Government Documents Department
The Breguet 270 General-Purpose Military Airplane (French) : A Two-Seat All-Steel Sesquiplane

The Breguet 270 General-Purpose Military Airplane (French) : A Two-Seat All-Steel Sesquiplane

Date: September 1, 1930
Creator: De Marolles, R J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls

Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls

Date: September 1, 1930
Creator: Hertel, Heinrich
Description: This report is intended to furnish bases for load assumptions in the designing of airplane controls. The maximum control forces and quickness of operation are determined. The maximum forces for a strong pilot with normal arrangement of the controls is taken as 1.25 times the mean value obtained from tests with twelve persons. Tests with a number of persons were expected to show the maximum forces that a man of average strength can exert on the control stick in operating the elevator and ailerons and also on the rudder bar. The effect of fatigue, of duration and of the nature (static or dynamic) of the force, as also the condition of the test subject (with or without belt) were also considered.
Contributing Partner: UNT Libraries Government Documents Department
Effects of the end fixation of airplane struts

Effects of the end fixation of airplane struts

Date: September 1, 1930
Creator: Teichmann, Alfred
Description: The main purpose of this report is to give references to literature on the subject of end fixation of airplane struts and also to furnish the constructor with a general survey of the simplest methods for estimating the end-fixation effect.
Contributing Partner: UNT Libraries Government Documents Department
Flight tests for the determination of static longitudinal stability

Flight tests for the determination of static longitudinal stability

Date: September 1, 1930
Creator: Blenk, Hermann
Description: The accuracy of the instruments used for flight test measurements has been inadequate so a new series of tests were commissioned with the development of an accurate elevator setting recorder.
Contributing Partner: UNT Libraries Government Documents Department
The Henderson "Hendy" 302 cabin airplane (British) : a two-seat low-wing cantilever monoplane

The Henderson "Hendy" 302 cabin airplane (British) : a two-seat low-wing cantilever monoplane

Date: September 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of airplane landing speeds

An investigation of airplane landing speeds

Date: September 1, 1930
Creator: Ridley, Kenneth F
Description: This paper describes an investigation on airplane landing speeds which was made to determine the applicability of accepted aerodynamic theory to the prediction of this particular performance characteristic. The experimental work consisted in measuring the landing speed of several monoplanes by a new photographic method. The results of these tests supplemented by available information regarding biplanes were compared with predictions made with basic aerodynamic theory. The prediction makes use of the fundamental relation between wing loading, lift coefficient, and speed of level flight, and the effects of aspect ratio and proximity to the ground on lift curve slope.
Contributing Partner: UNT Libraries Government Documents Department
Load assumptions for calculating the strength of airplanes

Load assumptions for calculating the strength of airplanes

Date: September 1, 1930
Creator: unknown
Description: The following load assumptions shall be taken as the basis of the strength calculations. Certain definite load conditions (e.g. of flight, control, landing and transport) shall be assumed. The loads shall be assumed to be safe loads, constant or only slowly variable, and the inertia forces due to elastic deformation are accordingly disregarded. The external forces, the force of gravity and the inertia forces on the whole airplane shall produce a condition of equilibrium.
Contributing Partner: UNT Libraries Government Documents Department