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Preliminary report on free flight tests

Description: Results are presented for a series of tests made by the Advisory Committee's staff at Langley Field during the summer of 1919 with the objectives of determining the characteristics of airplanes in flight and the extent to which the actual characteristics differ from those predicted from tests on models in the wind tunnel, and of studying the balance of the machines and the forces which must be applied to the controls in order to maintain longitudinal equilibrium.
Date: 1920
Creator: Warner, E. P. & Norton, F. H.
Partner: UNT Libraries Government Documents Department

Starting and performance characteristics of a large asymmetric supersonic free-jet facility

Description: Report presenting the characteristics of an asymmetric free-jet facility constructed to investigate a 48-inch-diameter ramjet engine and the associated asymmetric supersonic inlet and inlet diffuser. The design flow Mach number of 2.755 could not be established in the free-jet facility with dry inlet air at a temperature of 528 degrees Fahrenheit and overall pressure ratios up to 11.
Date: April 1, 1954
Creator: Seashore, Ferris L. & Hurrell, Herbert G.
Partner: UNT Libraries Government Documents Department

Supersonic nozzle design

Description: From Summary: "The theory of supersonic flow in nozzles is discussed, emphasis being placed on the physical rather than the mathematical point of view. Methods, both graphic and analytic, for designed nozzles are described together with a discussion of design factors. In addition, the analysis of given nozzle shapes to determine velocity distribution and possible existence of shock waves is considered."
Date: June 1948
Creator: Crown, J. Conrad
Partner: UNT Libraries Government Documents Department

Calibration Tunnel for High Speed

Description: For the investigation of measuring instruments at higher speeds up to a Mach number 0.7 a tunnel with closed test section was built in 1942 which was as simple and cheap as possible. The blower was a radial blower with straight sheet vanes of 800-millimeter diameter the tips of which were bent backward a little. The blower sucks the air through a honeycomb of diameter 1.2 meter with wide meshes. The air is then accelerated in a short cone with smooth transition to the test section. The cylindrical test section of 200-millimeter diameter has two windows (which are displaced 180 deg from each other. The instruments may be introduced and observed through and observed through these windows. The cross section is then enlarged by a straight diffuser 3.5 meters long and reaches the ninefold cross section. The air flows back into the room through a disk diffuser of 2-meter diameter. The maximum speed in the jet is 250 m/s for a drive power of 35 kT., if there are no installations in the jet. The velocity is determined by pressure holed along the test section.
Date: October 1946
Creator: Pretsch, J.
Partner: UNT Libraries Government Documents Department

Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number

Description: Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
Date: March 1950
Creator: Neihouse, Anshal I. & Pepoon, Philip W.
Partner: UNT Libraries Government Documents Department

Comparison of semispan and full-span tests of A 47.5 degrees sweptback wing with symmetrical circular-arc sections and having drooped-nose flaps, trailing-edge flaps, and ailerons

Description: Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.
Date: December 5, 1951
Creator: Lipson, Stanley & Barnett, U. Reed, Jr.
Partner: UNT Libraries Government Documents Department

Spark plug defects and tests

Description: The successful operation of the spark plug depends to a large extent on the gas tightness of the plug. Part 1 of this report describes the method used for measuring the gas tightness of aviation spark plugs. Part 2 describes the methods used in testing the electrical conductivity of the insulation material when hot. Part 3 describes the testing of the cold dielectric strength of the insulation material, the resistance to mechanical shock, and the final engine test.
Date: 1920
Creator: Silsbee, F. B.; Loeb, L. B.; Sawyer, L. G.; Fonseca, E. L.; Dickinson, H. C. & Agnew, P. G.
Partner: UNT Libraries Government Documents Department

An investigation of aircraft heaters XXXIV: experimental determination of thermal and hydrodynamical behavior of air flowing between a flat and a wave-shaped plate

Description: Report presenting an investigation of the thermal and hydrodynamical behavior of air flowing along a passage with one flat side, which was steam-heated, and one wave-shaped side, which was unheated. Two series of tests were conducted, one with the plates in direct opposition and one with the plates slightly separated, which induced turbulence upstream of the thermal boundary layer. Results regarding heat transfer and static-pressure drop are provided.
Date: August 1951
Creator: Boelter, Llewellyn Michael Kraus; Sanders, V. D.; Young, George; Morgan, M. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department

NACA Conference on Aircraft Loads

Description: This document contains reproductions of technical papers on some of the recent research results from the NACA Laboratories in the field of aircraft loads. These papers were presented at the NACA Conference on Aircraft Loads held at the Langley Memorial Aeronautical Laboratory, February 18 and 19, 1948. The primary purpose of this conference was to convey these research results to the military services and their airplane contractors and to provide those attending an opportunity for discussion of the results. The papers in this document were prepared for presentation at the conference and are considered as complementary to, rather than as substitutes for, the Committee's more complete and formal reports.
Date: 1948-02-18/1948-02-19
Partner: UNT Libraries Government Documents Department

Influence of refraction on the applicability of the Zehnder-Mach interferometer to studies of cooled boundary layers

Description: Report presenting an analytical investigation to determine the applicability of the Zehnder-Mach interferometer to two-dimensional cooled-boundary-layer studies. The main factor governing a test section design other than flow characteristics is the estimate of how close to the wall the boundary layer need be studied.
Date: September 1951
Creator: Kinsler, Martin R.
Partner: UNT Libraries Government Documents Department

A preliminary investigation of the power requirements of slotted test sections

Description: Report presenting an investigation of the power requirements for slotted tunnels and methods of reducing these requirements. All pressure losses reported occurred in the region between the upstream end of the entrance ball and the entrance to the diffuser and in handling air taken in through the slotted wall. Results regarding auxiliary pumping and ejector pumping are provided.
Date: July 7, 1953
Creator: Dennard, John S.
Partner: UNT Libraries Government Documents Department

Extract from a report on the resistance of spheres of small diameter in an airstream of high velocity

Description: Much attention is given here to the design of the wind tunnel and the experimental set-up. In comparing their results on the wind resistance of spheres to the results of other researchers, the authors find wide discrepancies. They are unable to explain the cause of the discrepancies, concluding, as they do, that the differing results could not be explained by the action of the wind tunnel walls.
Date: March 1921
Creator: Toussaint & Hayer
Partner: UNT Libraries Government Documents Department

Characteristics of loads in rough air at transonic speeds of rocket-powered models of a canard and a conventional-tail configuration

Description: Report presenting results from flight tests at transonic speeds for a canard and a conventional-tail rocket-powered model in continuous rough air. The use of an airspeed-fluctuation instrument for measuring the turbulence intensity experienced is described as well as the resulting improvement in the technique of testing rocket models in rough air. The short-period frequency was dominant in the center-of-gravity normal-acceleration response for both models.
Date: March 1, 1955
Creator: Vitale, A. James
Partner: UNT Libraries Government Documents Department

Investigations and Tests in the Towing Basin at Guidonia

Description: The experimental methods at the Guidonia towing basin are discussed including specifications. Some of the components examined are the bridge towing carriage, side towing carriage, catapult installation, and dynamometer systems. Tests were performed on hulls and floats, as well as motor boats and torpedo shaped bodies. Theoretical investigations were also performed to determine pressure distributions on geometrically simple bodies, propagation of small wave motions, and planing and submerged surfaces.
Date: April 1939
Creator: Cremona, C.
Partner: UNT Libraries Government Documents Department

A Method for the Instantaneous Determination of the Velocity and Direction of the Wind

Description: The laboratory instruments, which we often constructed with makeshift means, gave encouraging results and showed that they could satisfactorily meet the required conditions. By limiting ourselves to the employment of hot wires of 0.05 mm (0.002 in.) diameter, we obtained instruments which faithfully followed all the wind fluctuations of over 0.1 second and even much more rapid variations without any very great error.
Date: June 1924
Creator: Huguenard, E.; Magnan, A. & Planiol, A.
Partner: UNT Libraries Government Documents Department

Method of Curved Models and Its Application to the Study of Curvilinear Flight of Airships: Part 1

Description: In the first part of this paper we shall present the theoretical side of the problem of constructing curved model forms and the method of testing the model. In the second part we shall present a detailed account of the first experiments according to the given method, carried out with a curved model of the nonrigid airship V-2, and a comparison of the experimental results with some data of full-scale tests made with this airship in 1933.
Date: June 1937
Creator: Gourjienko, G. A.
Partner: UNT Libraries Government Documents Department

Resume of the Activities of the Aeronautical Experimental Institute, Rome, During the Months of May, June, July and August 1921

Description: This report is a listing of the different studies conducted by the Institute in May thru August of 1921. The aerodynamical section studied: the aerodynamical characteristics of a very thick concave-convex wing; the disturbance caused in a tunnel by the presence of a disk, placed in relation with a transversely infinite barrier; vertical pressure in a wing of low head resistance; the drag caused by two small doors in the sides of the fuselage. Some other studies conducted by the Institute included: depressions in the interior of the model of a wing; the influence of a conical casing fitted with helicoidal flanges centered on the hub of the propeller; the influence of the velocity of translation on the aerodynamical effects of the propeller; and the influence of a honeycomb placed in the tunnel.
Date: July 1922
Partner: UNT Libraries Government Documents Department

The Design of a Miniature Solid-Propellant Rocket

Description: "A miniature rocket motor was designed and developed to produce 3 ounces of thrust for a duration of 2 seconds. The rocket is simply designed, safe to operate, easily handled, and gives reproducible performance. Standard solid-propellant-rocket design techniques were found to be not wholly applicable to the design of miniature rockets because of excessive heat losses" (p. 1).
Date: March 1956
Creator: Heitkotter, Robert H.
Partner: UNT Libraries Government Documents Department

Flight Tests on Airplanes

Description: This report presents test procedures, methods, and instruments for flight testing of aircraft. Dynamic-pressure gauges are discussed at length.
Date: April 1926
Creator: Koppe, Heinrich
Partner: UNT Libraries Government Documents Department

Method Rendering It Possible, in Testing Airplane Wing Models at the Eiffel Laboratory, to Obtain Comparable Polars, Whether the Supports Are Attached to the Upper or Lower Side of Model

Description: Report presenting an examination of the errors that result from testing an aircraft model and applying the results to full-sized airplanes. An investigation is carried out to determine how to obtain comparable polars regardless of whether the supports are attached to the upper or lower side of the model.
Date: November 1922
Creator: Eiffel, G.
Partner: UNT Libraries Government Documents Department