Technical Report Archive & Image Library (TRAIL) - 134 Matching Results

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The resistance of spheres in wind tunnels and in air

Description: From Summary: "A satisfactory confirmation of Reynolds law has been accomplished, the effect of means of support determined, the range of experiment greatly extended by work in the new variable density wind tunnel, and the effects of turbulence investigated by work in the tunnels and by towing and dropping tests in free air. It is concluded that the erratic nature of most of the previous work is due to support interference and differing turbulence conditions. While the question of support has b… more
Date: 1924
Creator: Bacon, D. L. & Reid, E. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Relation of Fuel-Air Ratio to Engine Performance

Description: The tests upon which this report is based were made at the Bureau of Standards between October 1919 and May 1923. From these it is concluded that: (1) with gasoline as a fuel, maximum power is obtained with fuel-air mixtures of from 0.07 to 0.08 pound of fuel per pound of air; (2) maximum power is obtained with approximately the same ratio over the range of air pressures and temperatures encountered in flight; (3) nearly minimum specific fuel consumption is secured by decreasing the fuel conten… more
Date: 1924
Creator: Sparrow, Stanwood W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Distribution of Lift Over Wing Tips and Ailerons

Description: "This investigation was carried out in the 5-foot wind tunnel of the Langley Memorial Aeronautical Laboratory for the purpose of obtaining more complete information on the distribution of lift between the ends of wing spars, the stresses in ailerons, and the general subject of airflow near the tip of a wing. It includes one series of tests on four models without ailerons, having square, elliptical, and raked tips respectively, and a second series of positively and negatively raked wings with ai… more
Date: 1924
Creator: Bacon, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Complete Study of Longitudinal Oscillation of a VE-7 Airplane

Description: "This investigation was carried out by the National Advisory Committee for Aeronautics at Langley Field in order to study as closely as possible the behavior of an airplane when it was making a longitudinal oscillation. The airspeed, the altitude, the angle with the horizon and the angle of attack were all recorded simultaneously and the resulting curves plotted to the same time scale. The results show that all the curves are very close to damped sine curves, with the curves for height and angl… more
Date: 1924
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The vertical, longitudinal, and lateral accelerations experienced by an S. E. 5a airplane while maneuvering

Description: "This investigation was carried out by the Langley Field Laboratory of the National Advisory Committee for Aeronautics for the purpose of measuring the accelerations along the three principal axes of an airplane while it was maneuvering. The airplane selected for this purpose was the fairly maneuverable SE-5A and the instruments used were the NACA three component accelerometer and the NACA recording airspeed meter. The results showed that the normal accelerations did not exceed 4.000 G. While t… more
Date: 1924
Creator: Norton, F. H. & Carroll, T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Inertial Coefficients of an Airship in a Frictionless Fluid

Description: This report deals with the investigation of the apparent inertia of an airship hull. The exact solution of the aerodynamical problem has been studied for hulls of various shapes and special attention has been given to the case of an ellipsoidal hull. In order that the results for this last case may be readily adapted to other cases, they are expressed in terms of the area and perimeter of the largest cross section perpendicular to the direction motion by means of a formula involving a coefficie… more
Date: 1924
Creator: Bateman, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Measurement of the Damping in Roll on a JN4h in Flight

Description: "This investigation was carried out by the National Advisory Committee for Aeronautics for the purpose of measuring the value of L sub P in flight. The method consisted in flying with heavy weights on each wing tip, suddenly releasing one of them, and allowing the airplane to roll up to 90 degrees with controls held in neutral while a record was being taken of the airspeed, and angular velocity about the X axis. The results are of interest as they show that the damping found in the wind tunnel … more
Date: 1924
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Airfoil Thickness and Plan Form on Lateral Control

Description: This investigation was carried out for the purpose of determining the effectiveness of ailerons and tests were made on six model airfoils in the no. 1 wind tunnel of the National Advisory Committee for Aeronautics. The method consisted in measuring the rolling moments and aileron moments in the ordinary way.The results show that the thickness of the airfoil has very little effect on either the rolling moment or the hinge moment, although the resulting efficiency is somewhat higher for the taper… more
Date: 1924
Creator: Hoot, H. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Study of Longitudinal Dynamic Stability in Flight

Description: "This investigation was carried out by the aerodynamic staff of the National Advisory Committee for Aeronautics for the purpose of studying experimentally the longitudinal dynamic stability of airplanes in flight. The airplanes selected for this purpose were a standard rigged VE-7 advanced-training airplane and a JN4H with special tail surfaces. The airplanes were caused to oscillate by means of the elevator, then the longitudinal control was either locked or kept free while the oscillation die… more
Date: 1924
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engine performance and the determination of absolute ceiling

Description: From Summary: "This report contains a brief study of the variation of engine power with temperature and pressure. The variation of propeller efficiency in standard atmosphere is obtained from the general efficiency curve which is developed in NACA report no. 168. The variation of both power available and power required are then determined and curves plotted, so that the absolute ceiling may be read directly from any known sea-level value of the ratio of power available to power required."
Date: January 1924
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Stability as Affected by the Longitudinal Moment of Inertia

Description: "In a recent Technical Note (NACA-TN-115, October, 1922), Norton and Carrol have reported experiments showing that a relatively large (15 per cent) increase in longitudinal moment of inertia made no noticeable difference in the stability of a standard SE-5A airplane. They point out that G. P. Thomson, "Applied Aeronautics," page 208, stated that an increase in longitudinal moment of inertia would decrease the stability. Neither he nor they make any theoretical forecast of the amount of decrease… more
Date: 1924
Creator: Wilson, Edwin B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Reliable formulae for estimating airplane performance and the effects of changes in weight, wing area, or power

Description: This report contains the derivation and the verification of formulae for predicting the speed range ratio, the initial rate of climb, and the absolute ceiling of an airplane. Curves used in the computation are given in NACA-TR-171. Standard formulae for service ceiling, time of climb, cruising range, and endurance are also given in the conventional forms.
Date: January 1924
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Small Angular Oscillations of Airplanes in Steady Flight

Description: "This investigation was carried out by the National Advisory Committee for Aeronautics at the request of the Army Air Service to provide data concerning the small angular oscillations of several types of airplanes in steady flight under various atmospheric conditions. The data are of use in the design of bomb sights and other aircraft instruments. The method used consisted in flying the airplane steadily in one direction for at least one minute, while recording the angle of the airplane with th… more
Date: 1924
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Slipstream Obstructions on Air Propellers

Description: "The screw propeller on airplanes is usually placed near other objects, and hence its performance may be modified by them. Results of tests on propellers free from slip stream obstructions, both fore and aft, are therefore subject to correction, for the effect of such obstructions and the purpose of the investigation was to determine the effect upon the thrust and torque coefficients and efficiency, for previously tested air propellers, of obstructions placed in the slip stream, it being realiz… more
Date: 1924
Creator: Lesley, E. P. & Woods, B. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Relative efficiency of direct and geared drive propellers

Description: This report is an extension of NACA-TR-168 and has been prepared for the National Advisory Committee for Aeronautics to show the relative values of various direct and geared drives. It is well known that in general a geared-down propeller has higher efficiency than a direct-drive propeller, but the literature on this subject does not present the data in such form that the aeronautical engineer can readily visualize the effect of gearing. This report has been prepared to show the actual net gain… more
Date: January 1924
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Provisional Rules for the Inspection of Aircraft Adopted by the French Bureau Veritas

Description: These new regulations are intended to replace those of November 1, 1922, and give the directions to be followed in the supervision of aircraft by the agents of the Aeronautical Section of the Bureau Veritas. The rules consist of four sections: rules regarding an aircraft leaving a repair shop, the objects of quarterly and weekly inspections, and rules regarding the upkeep and repair of airplanes.
Date: September 1924
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of the hull and of the car-suspension systems of airships

Description: Differential and integral curves are presented and well as numerous calculations relating to hulls. Some of the calculations include those relating to hulls, those relating to the invariability of the shape of the hulls, and those relating to the suspension of the hull.
Date: October 1924
Creator: Verduzio, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The American Airship ZR-3

Description: This airship was built by the Zeppelin Airship Company at Friedrichshafen in 1923-4, for the United States Navy, as the reparations service of the German Government in fulfillment of the treaty of peace. A description of the design, components, flight characteristics, blueprints, and photographs are provided.
Date: November 1924
Creator: Dürr, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stieber Dynamometer Hub for Aircraft Propellers

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.
Date: November 1924
Creator: Stieber, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-Seat Light Airplanes Which Participated in Contest Held at Lympne, England, Week of September 29 to October 4, 1924

Description: Memorandum presenting a description of a competition to produce an airplane suitable for school work. The characteristics evaluated included the speed range, take off, landing, reliability, and high and low speed are provided. A variety of monoplanes and biplanes were entered and a description of each and their blueprints are provided.
Date: November 1924
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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