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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Collection: Technical Report Archive and Image Library
Standardization tests of NACA no. 1 wind tunnel

Standardization tests of NACA no. 1 wind tunnel

Date: January 1, 1925
Creator: Reid, Elliott G
Description: The tests described in this report were made in the 5-foot atmospheric wind tunnel of the National Advisory Committee for Aeronautics, at Langley Field. The primary objective of collecting data on the characteristics of this tunnel for comparison with those of others throughout the world, in order that, in the future, the results of tests made in all the principle laboratories may be interpreted, compared, and coordinated on a basis of scientifically established relationships, a process hitherto impossible due to the lack of comparable data. The work includes tests of a disk, spheres, cylinders, and airfoils, explorations of the test section for static pressure and velocity distribution, and determination of the variations of air flow direction throughout the operating range of the tunnel. (author).
Contributing Partner: UNT Libraries Government Documents Department
Static soaring flight over flat sea coasts

Static soaring flight over flat sea coasts

Date: November 1, 1923
Creator: Georgii, W
Description: Static soaring flight has hitherto been accomplished by means of two sources of energy: ascending air currents in the vicinity of obstacles and those produced by unequal heating. The latter has not yet been practically tested in soaring flight.
Contributing Partner: UNT Libraries Government Documents Department
Static stability of seaplane floats and hulls

Static stability of seaplane floats and hulls

Date: March 1, 1924
Creator: Diehl, W S
Description: Values of lateral and longitudinal metacentric heights for various seaplanes were calculated by means of approximate formulae derived here. The data are given in tabular form. Upon plotting these metacentric heights against the corresponding gross weights, it appears that the metacentric height is approximately a straight line function of the gross weight. For the lateral metacentric height GM = 13 + .002 W and for longitudinal metacentric height GM = 15 + .002 W, GM is in feet and the gross weight (W) is in pounds. Although only approximate, it is thought that the values indicated here are a reliable guide to current practice. It is recommended that the longitudinal and lateral metacentric heights be made equal and of the value given by GM = 15 = .002 W. The proper length or spacing required to satisfy the indicated value may then be obtained from substitution in the approximate formulae for metacentric height.
Contributing Partner: UNT Libraries Government Documents Department
Static testing and proposed standard specifications

Static testing and proposed standard specifications

Date: July 1, 1920
Creator: Warner, E P
Description: Static tests fall into two groups, the first of which is designed to load all members of the structure approximately in accordance with the worst loads which they carry in flight, while the second is directed to the testing of specific members which are suspected of weakness and which are difficult to analyze mathematically. The nature of the loading in the second type is different for every different test, but the purpose of the first is defined clearly enough to permit the adoption of some standard set of loading specifications, at least for airplanes of normal design. Here, an attempt is made to carry through an analysis leading to such a standard, the goal being the determination of a load which will simultaneously impose on every member of the airplane structure a stress equal to the worst it will carry in flight.
Contributing Partner: UNT Libraries Government Documents Department
Statical longitudinal stability of airplanes

Statical longitudinal stability of airplanes

Date: January 1, 1921
Creator: Warner, Edward P
Description: This report, which is a continuation of the "Preliminary report on free flight testing" (report no. NACA-TR-70), presents a detailed theoretical analysis of statical stability with free and locked controls and also the results of many free flight test on several types of airplanes. In developing the theory of stability with locked controls an expression for pitching moment is derived in simple terms by considering the total moment as the sum of the moments due to wings and tail surface. This expression, when differentiated with respect to angle of incidence, enables an analysis to be made of the factors contributing to the pitching moment. The effects of slipstream and down wash are also considered and it is concluded that the C. G. Location has but slight effect or stability, and that stability is much improved by increasing the efficiency of the tail surfaces, which may be done by using an "inverted" tail plane. The results of free flight tests with locked controls are discussed at length and it is shown that the agreement between the experimental results and theory is very satisfactory. The theory of stability with free controls is not amendable to the simple mathematical treatment used in the ...
Contributing Partner: UNT Libraries Government Documents Department
The steadiness factor in engine sets

The steadiness factor in engine sets

Date: January 1, 1920
Creator: Margoulis, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Steam power plants in aircraft

Steam power plants in aircraft

Date: June 1, 1926
Creator: Wilson, E E
Description: The employment of steam power plants in aircraft has been frequently proposed. Arguments pro and con have appeared in many journals. It is the purpose of this paper to make a brief analysis of the proposal from the broad general viewpoint of aircraft power plants. Any such analysis may be general or detailed.
Contributing Partner: UNT Libraries Government Documents Department
Steel spars

Steel spars

Date: April 1, 1928
Creator: Martin, Brian L
Description: A history of English metal spar construction is presented in this paper.
Contributing Partner: UNT Libraries Government Documents Department
Stieber dynamometer hub for aircraft propellers

Stieber dynamometer hub for aircraft propellers

Date: November 1, 1924
Creator: Stieber, W
Description: The knowledge gained from previous experiments and reports was utilized for the construction of a dynamometer hub for 200 mkg (134.4 ft.-lb.) and 1200 kg (2646 lb.) thrust suited for a Liberty "12" engine. A reversing device is also described.
Contributing Partner: UNT Libraries Government Documents Department
Stinson commercial airplane, type S M-1

Stinson commercial airplane, type S M-1

Date: October 1, 1927
Creator: unknown
Description: The Stinson S M-1 seats 5 passengers and a pilot. It is equipped with a Wright Whirlwind Engine.
Contributing Partner: UNT Libraries Government Documents Department