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Rules and Regulations for Endurance Contest of Aviation Engines: Under the Auspices of the Aero Club of France
Memorandum presenting the rules and regulations of the Endurance Contest of Aviation Engines, which was put on by the Aero Club of France. A description of the rules regarding the aircraft in competition, the characteristics of the tests that were conducted, and information regarding classification of the aircraft is provided.
Date:
November 1923
Creator:
unknown
System:
The UNT Digital Library
Static Soaring Flight Over Flat Sea Coasts
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.
Date:
November 1923
Creator:
Georgii, W.
System:
The UNT Digital Library
Tests on Riveted Joints in Sheet Duralumin
In making tension tests, the slippage of the joints was noted at three points across each joint. In addition, stress strain curves were obtained for plain tension specimens, and a chemical analysis was made of the sheet.
Date:
November 1923
Creator:
Rettew, H. F. & Thumin, G.
System:
The UNT Digital Library
Wind Tunnel Tests of Five Strut Sections in Yaw
In the first series of wind tunnel tests, the drag and cross wing force of all the struts were measured at a wind speed of 30 mph and at angles of yaw from 0 degrees to 20 degrees. To determine the magnitude of the VL effect, each strut was tested at zero yaw and at a series of speeds ranging from 15 to 38 mph. Although designed as fairings for cables, part of these sections gave such high crosswind forces that they seemed to have possibilities as airfoils.
Date:
November 1923
Creator:
Warner, Edward P.
System:
The UNT Digital Library
The American Airship ZR-3
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.
System:
The UNT Digital Library
Effect of Altitude on Power of Aviation Engines
"These notes are intended to furnish practical and general data on the effect of altitude on engine power. The effective horsepower of an engine is a function of the mean pressure of the fluid acting on the pistons, of the R.P.M. of the engine and of the mechanical efficiency" (p. 1).
Date:
November 1924
Creator:
Raffaelli, Italo
System:
The UNT Digital Library
The Simplifying Assumptions, Reducing the Strict Application of Classical Hydrodynamics to Practical Aeronautical Computations
Note presenting a general method followed to simplify the numerical work in hydrodynamics, which consists of neglecting quantities of a lower order of magnitude. Four of the solutions covered in this report include the theory of the lateral air forces on airship hulls, theory of wing sections in a two-dimensional flow, theory of wings with a finite span, and propeller theory.
Date:
November 1924
Creator:
Munk, Max M.
System:
The UNT Digital Library
Stieber Dynamometer Hub for Aircraft Propellers
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.
System:
The UNT Digital Library
Structural Weight of Aircraft as Affected by the System of Design
Various details of design or arrangement of the parts of airplane structures are shown and discussed, the use of these devices having resulted in the production of structures of adequate strength, yet of a weight less than one-half of the usual construction.
Date:
November 1924
Creator:
Hall, Charles Ward
System:
The UNT Digital Library
Tests on Duralumin Columns for Aircraft Construction
The following paper is based on the results of tests, upon duralumin columns, contained in two theses presented to the Department of Civil and Sanitary Engineering of the Massachusetts Institute of Technology.
Date:
November 1924
Creator:
Lee, John G.
System:
The UNT Digital Library
Two-Seat Light Airplanes Which Participated in Contest Held at Lympne, England, Week of September 29 to October 4, 1924
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
Creator:
unknown
System:
The UNT Digital Library
An Altitude Chamber for the Study and Calibration of Aeronautical Instruments
"The design and construction of an altitude chamber, in which both pressure and temperature can be varied independently, was carried out by the NACA at the Langley Memorial Aeronautical Laboratory for the purpose of studying the effects of temperature and pressure on aeronautical research instruments. Temperatures from +20c to -50c are obtained by the expansion of CO2from standard containers. The chamber can be used for the calibration of research instruments under altitude conditions simulating those up to 45,000 feet" (p. 1).
Date:
November 1925
Creator:
Reid, H. J. E. & Kirchner, Otto E.
System:
The UNT Digital Library
A Method for the Direct Determination of Wing-Section Drag
In order that the method may be more easily understood, we will first consider the simpler case when there is no lift, but only drag, and when the streamlines at the measuring point behind the obstacle are nearly parallel. Moreover, the flow is assumed not to deviate much from the two-dimensional flow.
Date:
November 1925
Creator:
Betz, A.
System:
The UNT Digital Library
Recent Progress in the Theoretical Deduction of Airplane Wings
The designing of an airplane requires an accurate knowledge of the aerodynamic properties of its wings, as expressed in the polar diagram. It is important to continue the theoretical researches on the aerodynamic phenomena of wings, in order to determine by calculation, their fundamental characteristics and to increase and formulate our knowledge in this field.
Date:
November 1925
Creator:
Panetti, M.
System:
The UNT Digital Library
The A.N.E.C. IV "Missel Thrush" light airplane
A product of the Air Navigation Engineering Co., the Missel Thrush is a light airplane suitable for private ownership. It is a two seat tractor fuselage biplane with single I interplane struts designed by J. Bewsher.
Date:
November 1926
Creator:
United States. National Advisory Committee for Aeronautics.
System:
The UNT Digital Library
Approximate Calculation of the Static Longitudinal Stability of Airplanes
It seems desirable to have some simple method for calculating quickly and with sufficient accuracy: 1) the correct position of the center of gravity; 2) the requisite tail-group dimensions; 3) and the course of the wing and tail-group moments. In out deductions, we will first replace the biplane (disregarding the effect of stagger, decalage and induced drag) by an equivalent monoplane, whose dimensions and position in space can be approximately determined in a simple manner.
Date:
November 1926
Creator:
Bienen, Theodor
System:
The UNT Digital Library
Avia Pursuit Airplane B.H. 21
Built by the 'Czecho-Slovakian' aircraft factory, AVIA, the B.H. 21, has a top speed of 250 MPH, and carries 120 kg of gasoline and 20 kg of oil, giving it a radius of action of 600-650 km. It is equipped with a Hispano-Suiza engine capable of 300 HP. Details of the design, structure, wings, stabilizer, fuselage, controls, fuel tanks, landing gear, tail, characteristics, performances, drawings, and photographs are provided.
Date:
November 1926
Creator:
Serryer, J.
System:
The UNT Digital Library
Central Aerohydrodynamic Institute of Moscow, Russia
The staff and construction of the Institute are described as well as a variety of experiments and researches being conducted there. The six sections of the laboratory are described, including the Section for Theoretical Researches, Section for Aerodynamic Researches, Windmill Section, Section for Engine-Propeller Groups, Section for Material Testing, and Section for Instrument Making. Special attention is given to the various wind tunnels and testing facilities present.
Date:
November 1926
Creator:
Margoulis, W.
System:
The UNT Digital Library
Devices for Prevention of Stalled Flight
Memorandum describing warning or correcting devices based on the registering of two distinct factors, the air speed and the angle of attack. The authors of the report define the conditions for the flight of an airplane and then study the causes of stalled flight in the different cases where it can occur.
Date:
November 1926
Creator:
Mazer, Paul
System:
The UNT Digital Library
The effect of tube length upon the recorded pressures from a pair of static orifices in a wing panel
Report presenting an investigation to determine the effect of tubing length on the indicated pressure values as ascertained in the pressure distribution measurements on the PW-9. The purpose was to determine the percentage of error in the pressure readings which might be caused by various lengths of tubing between the pressure orifices and pressure cell at the manometer. The differences in head caused by variations in the length of tubing are small, the lowest recorded being zero, the highest 2.7 percent.
Date:
November 1926
Creator:
Carroll, T. & Mixon, R. E.
System:
The UNT Digital Library
Experiments With a Sphere From Which the Boundary Layer Is Removed by Suction
The task of removing the boundary layer by suction consists in producing, in place of the ordinary flow with the formation of vortices, another kind of flow in which the vortices are eliminated by drawing small quantities of fluid from certain points on the surface into the interior of the body. The experiments with a sphere, which constitute the subject of this report, were made early in the present year .
Date:
November 1926
Creator:
Schrenk, Oskar
System:
The UNT Digital Library
The Handley Page "Hamlet"
The Hamlet is a three engine high wing monoplane of comparatively small size, fitted with three Bristol Lucifer series IV engines of 130 HP. each, and designed to carry a pilot and four passengers. Details of the layout, wings, slot and flap gear, fuselage, characteristics, performance, and drawings are provided.
Date:
November 1926
Creator:
unknown
System:
The UNT Digital Library
Influence of the Orifice on Measured Pressures
"The influence of different orifices on the result of measuring the same pressure distributions is the subject of this note. A circular cylinder is exposed to an air stream perpendicular to its axis and its pressure distribution is repeatedly determined. The pressures measured on the downstream half of the cylinder do not change for the orifice sizes used in the tests" (p. 1).
Date:
November 1926
Creator:
Hemke, Paul E.
System:
The UNT Digital Library
Air force and moment for N-20 wing with certain cut-outs
From Introduction: "The airplane designer often finds it necessary, in meeting the requirements of visibility, to remove area or to otherwise locally distort the plan or section of an airplane wing. This report, prepared for the Bureau of Aeronautics January 15, 1925, contains the experimental results of tests on six 5 by 30 inch N-20 wing models, cut out or distorted in different ways, which were conducted in the 8 by 8 foot wind tunnel of the Navy Aerodynamical Laboratory in Washington in 1924. The measured and derived results are given without correction for vl/v for wall effect and for standard air density, p=0.00237 slug per cubic foot."
Date:
November 29, 1926
Creator:
Smith, R. H.
System:
The UNT Digital Library