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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1925
 Collection: Technical Report Archive and Image Library
Accelerations in flight

Accelerations in flight

Date: January 1, 1925
Creator: Doolittle, J H
Description: This work on accelerometry was done at McCook Field for the purpose of continuing the work done by other investigators and obtaining the accelerations which occur when a high-speed pursuit airplane is subjected to the more common maneuvers. The accelerations obtained in suddenly pulling out of a dive with well-balanced elevators are shown to be within 3 or 4 per cent of the theoretically possible accelerations. The maximum acceleration which a pilot can withstand depends upon the length of time the acceleration is continued. It is shown that he experiences no difficulty under the instantaneous accelerations as high as 7.8 G., but when under accelerations in excess of 4.5 G., continued for several seconds, he quickly loses his faculties.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of aircraft with reference to their use

Aerodynamic characteristics of aircraft with reference to their use

Date: January 1, 1925
Creator: Panetti, M
Description: Economic and design characteristics are examined in the design of airplanes and airships.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils at high speeds

Aerodynamic characteristics of airfoils at high speeds

Date: January 1, 1925
Creator: Briggs, L J; Hull, G F & Dryden, H L
Description: This report deals with an experimental investigation of the aerodynamical characteristics of airfoils at high speeds. Lift, drag, and center of pressure measurements were made on six airfoils of the type used by the air service in propeller design, at speeds ranging from 550 to 1,000 feet per second. The results show a definite limit to the speed at which airfoils may efficiently be used to produce lift, the lift coefficient decreasing and the drag coefficient increasing as the speed approaches the speed of sound. The change in lift coefficient is large for thick airfoil sections (camber ratio 0.14 to 0.20) and for high angles of attack. The change is not marked for thin sections (camber ratio 0.10) at low angles of attack, for the speed range employed. At high speeds the center of pressure moves back toward the trailing edge of the airfoil as the speed increases. The results indicate that the use of tip speeds approaching the speed of sound for propellers of customary design involves a serious loss in efficiency.
Contributing Partner: UNT Libraries Government Documents Department
Air flow investigation for location of angle of attack head on a JN4h airplane

Air flow investigation for location of angle of attack head on a JN4h airplane

Date: August 1, 1925
Creator: Freeman, R G
Description: The technical staff of the NACA at Langley Field, has made a series of free flight tests with a JN4h airplane in order to find the best place for an instrument for measuring the angle of attack. A "neutral zone" was found where the air remains either at rest relative to the undisturbed air beyond the influence of the airplane, or is set in motion parallel to the motion of the airplane. This zone is about midway between the two wings and slightly in front of, or at the vertical plane through the leading edges of the wings but the exact position as well as the outlines of the zone varies considerably as the conditions of flight change.
Contributing Partner: UNT Libraries Government Documents Department
Air forces on airfoils moving faster than sound

Air forces on airfoils moving faster than sound

Date: June 1, 1925
Creator: Ackeret, J
Description: We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft engine design

Aircraft engine design

Date: January 1, 1925
Creator: Wilson, E E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airplane parachutes

Airplane parachutes

Date: August 1, 1925
Creator: Mazer,
Description: The "Bulletin Technique", of March, 1919, gave the results of tests and studies made up to that date in connection with airplane parachutes. This work has been continued.
Contributing Partner: UNT Libraries Government Documents Department
Alloys similar to duralumin made in other countries than Germany

Alloys similar to duralumin made in other countries than Germany

Date: May 1, 1925
Creator: Meissner, K L
Description: Attempts by other countries to develop patents for alloys similar to duralumin are presented. Duralumin is aluminum alloyed with 3.5-4.5% copper, 0.5% magnesium, and 0.25-1% of manganese.
Contributing Partner: UNT Libraries Government Documents Department
An altitude chamber for the study and calibration of aeronautical instruments

An altitude chamber for the study and calibration of aeronautical instruments

Date: November 1, 1925
Creator: Reid, J E & Kirchner, Otto E
Description: The design and construction of an altitude chamber, in which both pressure and temperature can be varied independently, was carried out by the NACA at the Langley Memorial Aeronautical Laboratory for the purpose of studying the effects of temperature and pressure on aeronautical research instruments. Temperatures from +20c to -50c are obtained by the expansion of CO2from standard containers. The chamber can be used for the calibration of research instruments under altitude conditions simulating those up to 45,000 feet. Results obtained with this chamber have a direct application in the design and calibration of instruments used in free flight research.
Contributing Partner: UNT Libraries Government Documents Department
Altitude of equilibrium of an airship

Altitude of equilibrium of an airship

Date: March 1, 1925
Creator: Nobile, Umberto
Description: This report details the procedure followed in establishing a general formula enabling the calculation of the maximum altitude attainable statically.
Contributing Partner: UNT Libraries Government Documents Department
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