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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Collection: National Advisory Committee for Aeronautics Collection
Sphere drag tests in the variable density wind tunnel

Sphere drag tests in the variable density wind tunnel

Date: August 1, 1929
Creator: Jacobs, Eastman N
Description: The air forces on a twenty-centimeter sphere were measured after it had been rebuilt as an open throat type. The results from tests made at widely different densities and airspeeds and also on a smaller sphere are given.
Contributing Partner: UNT Libraries Government Documents Department
Spindled and hollow spars

Spindled and hollow spars

Date: October 1, 1926
Creator: Blyth, J. D.
Description: The most usual method of arriving at the maximum amount of spindling or hollowing out permissible in the case of any particular spar section is by trial and error, a process which is apt to become laborious in the absence of good guessing - or luck. The following tables have been got out with the object of making it possible to arrive with certainty at a suitable section at the first attempt.
Contributing Partner: UNT Libraries Government Documents Department
Spiral tendency in blind flying

Spiral tendency in blind flying

Date: August 1, 1929
Creator: Carroll, Thomas & Mcavoy, William H
Description: The flight path followed by an airplane which was being flown by a blindfolded pilot was observed and recorded. When the pilot attempted to make a straight-away flight there was a tendency to deviate from the straight path and to take up a spiral one.
Contributing Partner: UNT Libraries Government Documents Department
Spontaneous combustion of hydrogen

Spontaneous combustion of hydrogen

Date: December 1, 1923
Creator: Pothmann, PH & Nusselt, Wilhelm
Description: It is shown by the author's experiments that hydrogen which escapes to the atmosphere through openings in the system may burn spontaneously if it contains dust. Purely thermal reasoning can not account for the combustion. It seems to be rather an electrical ignition. In order to determine whether the cause of the spontaneous ignition was thermo-chemical, thermo-mechanical, or thermo-electrical, the experiments in this paper were performed.
Contributing Partner: UNT Libraries Government Documents Department
Spray penetration with a simple fuel injection nozzle

Spray penetration with a simple fuel injection nozzle

Date: January 1, 1926
Creator: Miller, Harold E & Beardsley, Edward G
Description: The purpose of the tests covered by this report was to obtain specific information on the rate of penetration of the spray from a simple injection nozzle, having a single orifice with a diameter of 0.015 inch when injecting into compressed gases. The results have shown that the effects of both chamber and fuel pressures on penetration are so marked that the study of sprays by means of high-speed photography or its equivalent is necessary if the effects are to be appreciated sufficiently to enable rational analysis. It was found for these tests that the negative acceleration of the spray tip is approximately proportional to the 1.5 power of the instantaneous velocity of the spray tip.
Contributing Partner: UNT Libraries Government Documents Department
Stability equations for airship hulls

Stability equations for airship hulls

Date: January 1, 1926
Creator: Zahm, A. F.
Description: In the text are derived simple formulae for determining, directly from the data of wind tunnel tests of a model of an airship hull, what shall be the approximate character of oscillation, in pitch or yaw, of the full-scale airship when slightly disturbed from steady forward motion. (author).
Contributing Partner: UNT Libraries Government Documents Department
Stability of airplanes

Stability of airplanes

Date: May 1, 1922
Creator: Warner, Edward P
Description: The author attempts to correct the misconception that piloting an airplane requires extraordinary skill and balance. He also tries to show that airplanes are extremely stable in flight. Some of the major points covered in this article include: automatic pilots, airplanes designed to be stable, and the reliance on mathematics to help in designing stable aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Stability of the parachute and helicopter

Stability of the parachute and helicopter

Date: January 1, 1920
Creator: Batemen, H
Description: This report deals with an extension of the theory of stability in oscillation to the case of aircraft following a vertical trajectory, and particularly to the oscillations of parachutes.
Contributing Partner: UNT Libraries Government Documents Department
Stall-proof airplanes

Stall-proof airplanes

Date: January 1, 1927
Creator: Lachmann, G
Description: My lecture has to do with the following questions. Is the danger of stalling necessarily inherent in the airplane in its present form and structure, or can it be diminished or eliminated by suitable means? Do we possess such means or devices and how must they operate? In this connection I will devote special attention to the exhibition of stall-proof airplanes by Fokker under the auspices of the English Air Ministry, which took place in Croyden last April.
Contributing Partner: UNT Libraries Government Documents Department
Standard atmosphere

Standard atmosphere

Date: January 1, 1923
Creator: Gregg, Willis Ray
Description: This report was prepared at the request of the National Advisory Committee for Aeronautics and discusses the need of a standard set of values of pressure, temperature and density at various altitudes and points out the desirability of adopting such values as are most in accord with actual average conditions, in order that corrections in individual cases may be as small as possible. To meet this need, so far as the united states is concerned, all free-air observations obtained by means of kites and balloons at several stations in this country near latitude 40 degrees N., have been used, and average values of pressure, temperature, and density, based upon those observations, have been determined for summer, winter, and the year, and for all altitudes up to 20,000 meters (65,000 feet). These values are presented in tables and graphs in both metric and english units; and in the tables of densities there are also included values of density for other parts of the world, more particularly for Europe. A comparison with these values shows that, except in the lowest levels, the agreement is very satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
Standard atmosphere - tables and data

Standard atmosphere - tables and data

Date: January 1926
Creator: Diehl, Walter S.
Description: Detailed tables of pressures and densities are given for altitudes up to 20,000 meters and to 65,000 feet. In addition to the tables the various data pertaining to the standard atmosphere have been compiled in convenient form for ready reference. This report is an extension of NACA-TR-147.
Contributing Partner: UNT Libraries Government Documents Department
Standardization and aerodynamics

Standardization and aerodynamics

Date: March 1, 1923
Creator: Knight, William; Prandtl, L; VON KARMAN; Costanzi, G; Margoulis, W; Verduzio, R et al.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
Strength calculations on airplanes

Strength calculations on airplanes

Date: December 1, 1925
Creator: Baumann, A
Description: Every strength calculation, including those on airplanes, must be preceded by a determination of the forces to be taken into account. In the following discussion, it will be assumed that the magnitudes of these forces are known and that it is only a question of how, on the basis of these known forces, to meet the prescribed conditions on the one hand and the practical requirements on the other.
Contributing Partner: UNT Libraries Government Documents Department
The strength of one-piece solid, build-up and laminated wood airplane wing beams

The strength of one-piece solid, build-up and laminated wood airplane wing beams

Date: January 1, 1920
Creator: Nelson, John H
Description: The purpose of this report is to summarize the results of all wood airplane wing beams tested to date in the Bureau of Standards Laboratory in order that the various kinds of wood and methods of construction may be compared. All beams tested were of an I section and the majority were somewhat similar in size and cross section to the front wing beam of the Curtiss JN-4 machine. Construction methods may be classed as (1) solid beams cut from solid stock; (2) three-piece beams, built up of three pieces, web and flanges glued together by a tongue-and-groove joint and (3) laminated beams built up of thin laminations of wood glued together.
Contributing Partner: UNT Libraries Government Documents Department