Technical Report Archive and Image Library (TRAIL) - 1,424 Matching Results

Search Results

Airplane dopes and doping

Description: Report details some examples of dopes and doping on airplanes and balloons and the various properties of different materials. Topics covered include cellulose nitrate dopes, cellulose acetate dopes, dope covers, application of dopes, and fireproof dopes
Date: 1919
Creator: Smith, W. H.
Partner: UNT Libraries Government Documents Department

Airplane stress analysis

Description: Report presents stress analysis of individual components of an airplane. Normal and abnormal loads, sudden loads, simple stresses, indirect simple stresses, resultant unit stress, repetitive and equivalent stress, maximum steady load and stress are considered.
Date: January 1918
Creator: Zahm, A. F. & Crook, L. H.
Partner: UNT Libraries Government Documents Department

The airplane tensiometer

Description: Certain parts of an airplane are subjected not only to the stresses imposed by the aerodynamic or flying load, but also to the initial stresses, caused by the tension in the stay and drift wires. Report describes a tensiometer that measures such stresses which is simple in construction, accurate, and easily and quickly operated even by inexperienced persons. Two sizes of the instrument are available. One is suitable for wires up to one-fourth inch in diameter and the other for wires from one-fourth to three-eights inch in diameter.
Date: 1919
Creator: Larson, L. J.
Partner: UNT Libraries Government Documents Department

Airship model tests in the variable density wind tunnel

Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
Date: January 27, 1931
Creator: Abbott, Ira H
Partner: UNT Libraries Government Documents Department

An airship slide rule

Description: From Introduction: "This report prepared for the National Advisory Committee for Aeronautics, describes an airship slide rule developed by the Gas-Chemistry Section of the Bureau of Standards, at the request of the Bureau of Engineering of the Navy Department."
Date: 1924?~
Creator: Weaver, E. R. & Pickering, S. F.
Partner: UNT Libraries Government Documents Department

Alternating-current equipment for the measurement of fluctuations of air speed in turbulent flow

Description: From Summary: "Recent electrical and mechanical improvements have been made in the equipment developed at the National Bureau of Standards for measurement of fluctuations of air speed in turbulent flow. Data useful in the design of similar equipment are presented. The design of rectified alternating-current power supplies for such apparatus is treated briefly, and the effect of the power supplies on the performance of the equipment is discussed."
Date: March 1937
Creator: Mock, W. C., Jr.
Partner: UNT Libraries Government Documents Department

The altitude effect on air speed indicators

Description: The report present the results of a theoretical and experimental study of the effect, on the performance of air speed indicators, of the different atmospheric conditions experienced at various altitudes.
Date: 1917~
Creator: Hersey, M. D.; Hunt, F. L. & Eaton, H. N.
Partner: UNT Libraries Government Documents Department

The altitude effect on air speed indicators II

Description: In an investigation described in NACA Technical Report 110, it was shown that under certain conditions, particularly for the relatively low-speed flight of airships, the data obtained were not sufficiently accurate. This report describes an investigation in which the data obtained were sufficiently accurate and complete to enable the viscosity correction to be deduced quantitatively for a number of the air-speed pressure nozzles in common use. The report opens with a discussion of the theory of the performance of air-speed nozzles and of the calibration of the indicators, from which the theory of the altitude correction is developed. Then follows the determination of the performance characteristics of the nozzles and calibration constants used for the indicators. In the latter half of the report, the viscosity correction is computed for the Zahm Pitot-venturi nozzles.
Date: 1923?~
Creator: Eaton, H. N. & Macnair, W. A.
Partner: UNT Libraries Government Documents Department

Aluminum and its light alloys

Description: Report is a summary of research work which has been done here and abroad on the constitution and mechanical properties of the various alloy systems with aluminum.
Date: 1920?~
Creator: Merica, Paul D
Partner: UNT Libraries Government Documents Department

Analog study of interacting and noninteracting multiple-loop control systems for turbojet engines

Description: The results of an analog investigation of several turbojet-engine control configurations is presented in this report. Both proportional and proportional-plus-integral controllers were studied, and compensating terms for engine interaction were added to the control system. Data were obtained on the stability limits and the transient responses of these various configurations. Analytical expressions in terms of the component transfer functions were developed for the configurations studied, and the optimum form for the compensation terms was determined. It was found that the addition of the integral term, while making the system slower and more oscillatory, was desirable in that it made the final values of the system parameters independent of source of disturbance and also eliminated droop in these parameters. Definite improvement in system characteristics resulted from the use of proper compensation terms. At comparable gain points the compensated system was faster and more stable. Complete compensation eliminated engine interaction, permitting each loop to be developed to an optimum point independently.
Date: January 1, 1955
Creator: Pack, George J & Phillips, W E , Jr
Partner: UNT Libraries Government Documents Department

Analysis and calculation by integral methods of laminar compressible boundary-layer with heat transfer and with and without pressure gradient

Description: From Introduction: "The purpose of the present report is to present a comprehensive summary of theoretical investigations of comprehensible laminar boundary layers which have been carried out since 1949 at the Polytechnic Institute of Brooklyn under the sponsorship and with the financial assistance of the National Advisory Committee for Aeronautics. The results of these investigations are contained primarily in references 1 to 7."
Date: April 12, 1955
Creator: Morduchow, Morris
Partner: UNT Libraries Government Documents Department

Analysis and modification of theory for impact of seaplanes on water

Description: From Summary: "An analysis of available theory on seaplane impact and a proposed modification thereto are presented. In previous methods the overall momentum of the float and virtual mass has been assumed to remain constant during the impact but the present analysis shows that this assumption is rigorously correct only when the resultant velocity of the float is normal to the keel."
Date: January 1, 1945
Creator: Mayo, Wilbur L
Partner: UNT Libraries Government Documents Department

Analysis of 2-spar cantilever wings with special reference to torsion and load transference

Description: From Summary: "This paper deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined."
Date: January 1, 1936
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber

Description: From Introduction: "The difficulties experienced in cooling the exhaust-valve seats of the rear-row cylinders have been overcome to a considerable extent by improving the mixture distribution through application of the injection impeller (reference 1) and by augmenting the flow of cooling air to the critical baffles (reference 2). Flight tests of this airplane (reference 3) indicated that the temperatures of exhaust-valve seats on rear-row cylinders were markedly lowered by these modifications and that airplane range, altitude, and gross weight previously limited by these temperatures could be greatly increased."
Date: March 14, 1946
Creator: Marble, Frank E; Miller, Marlon A & Bell, E Barton
Partner: UNT Libraries Government Documents Department

Analysis of effect of basic design variables on subsonic axial-flow-compressor performance

Description: From Summary: "A blade-element theory for axial-flow compressors has been developed and applied to the analysis of the effects of basic design variables such as Mach number, blade loading, and velocity distribution on compressor performance. The relations among several efficiencies useful in compressor design are derived and discussed. The possible gains in useful operating range obtainable by the use of adjustable stator blades are discussed and a rapid approximate method of calculating blade-angle resettings is shown by an example."
Date: November 26, 1947
Creator: Sinnette, John T , Jr
Partner: UNT Libraries Government Documents Department

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Description: Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: July 21, 1942
Creator: Becker, John V & Baals, Donald D
Partner: UNT Libraries Government Documents Department

Analysis of jet-propulsion-engine combustion-chamber pressure losses

Description: From Summary: "The development and the use of a chart for estimating the pressure losses in jet-engine combustion chambers are described. By means of the chart, the pressure losses due to fluid friction and to momentum changes in the air flow accompanying combustion can be separately evaluated. The over-all pressure losses computed from the pressure-loss chart are within 7 percent of the experimental values for the three types of combustion chambers considered herein."
Date: July 31, 1946
Creator: Pinkel, I Irving & Shames, Harold
Partner: UNT Libraries Government Documents Department

An analysis of laminar free-convection flow and heat transfer about a flat plate paralled to the direction of the generating body force

Description: From Introduction: "Although the final equations obtained by this method are the same as those of Schmidt and Beckmann, this more general approach not only clearly demonstrates the significance of all the important parameters and assumptions and hence leads to a better understanding of this type of flow but also indicates the quantitative limitations of the theory. In addition, the numerical solutions of references 2 and 3 are herein extended to cover a more complete range of parameters."
Date: 1953~
Creator: Ostrach, Simon
Partner: UNT Libraries Government Documents Department

Analysis of landing-gear behavior

Description: From Summary: "This report presents a theoretical study of the behavior of the conventional type of oleo-pneumatic landing gear during the process of landing impact. The basic analysis is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection."
Date: 1953~
Creator: Milwitzky, Benjamin & Cook, Francis E
Partner: UNT Libraries Government Documents Department