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The Separation of Flow Due to Compressibility Shock
It is known that the compressibility shocks accompanying local or total supersonic flows lead to pronounced flow separations which result in unusually high energy losses on airplane wings, vanes, and in diffusers. These phenomena were investigated experimentally and theoretically.
Date:
July 1947
Creator:
Weise, A.
System:
The UNT Digital Library
Some Notes on Gasoline-Engine Development
Experiments were carried out using a special engine with small glass windows and a stroboscope to record various aspects of engine performance. Valve position, supercharging, and torque recoil were all investigated with this experimental apparatus.
Date:
July 1927
Creator:
Ricardo, H. H.
System:
The UNT Digital Library
The Stability of Orthotropic Elliptic Cylinders in Pure Bending
"The theoretical critical bending stress of elliptic cylindrical shells is determined on the assumption of infinite shell length and absence of local instability phenomena. The results of the tests on isotropic elliptic cylindrical shells stressed in bending are compared with the theoretical results. The practical applicability of the theory is discussed" (p. 1).
Date:
July 1937
Creator:
Heck, O. S.
System:
The UNT Digital Library
Stability of the Cylindrical Shell of Variable Curvature
"This report is a first attempt to devise a calculation method for representing the buckling behavior of cylindrical shells of variable curvature. The problem occurs, for instance, in dimensioning wing noses, the stability of which is decisively influenced by the variability of curvature. The calculation is made possible by simplifying the stability equations (permissible for the shell of small curvature) and by assuming that the curvature 1/R as a function of the arc lengths can be represented by a very few Fourier terms" (p. 1).
Date:
July 1951
Creator:
Marguerre, Karl
System:
The UNT Digital Library
Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients
"In reading the publications on turbulence of different authors, one often runs the risk of confusing the various correlation coefficients and turbulence spectra. We have made a point of defining, by appropriate concepts, the differences which exist between these functions. Besides, we introduce in the symbols a few new characteristics of turbulence" (p. 1).
Date:
July 1958
Creator:
Frenkiel, Francois N.
System:
The UNT Digital Library
The Steady Spin
With the object of further clarifying the problem of spinning, the equilibrium of the forces and moments acting on an airplane is discussed in light of the most recent test data. Convinced that in a spin the flight attitude by only small angles of yaw is more or less completely steady, the study is primarily devoted to an investigation of steady spin with no side slip. At small angles, wholly arbitrary and perfectly steady spins may be forced, depending on the type of control displacements. But at large angles only very steep and only "approaching steady" spins are possible, no matter what the control displacements.
Date:
July 1931
Creator:
Fuchs, Richard & Schmidt, Wilhelm
System:
The UNT Digital Library
Stresses Developed in Seaplanes While Taking Off and Landing
In the case of seaplanes, the lack of elastic shock absorbers, the presence of which might be quite dangerous, especially in taking off, makes it necessary to give some consideration to the phenomenon of landing. Special consideration must be given the process of taking off, since even moderately rough water may develop rather large stresses. The purpose of this communication is to show what has been accomplished in Italy and other countries and to draw a few useful conclusions.
Date:
July 1932
Creator:
Verduzio, Rudolfo
System:
The UNT Digital Library
The Stresses in Columns Under Combined Axial and Side Loads
The problem before us is to determine the total stresses in an axially loaded column of any degree of restraint which is also subject to transverse bending both from a uniformly distributed load and from concentrated loads. The solution of this problem is of special importance in the design of aircraft which consist of slender columns" (p. 1).
Date:
July 1922
Creator:
Arnstein, Karl & Truscott, Starr
System:
The UNT Digital Library
The Structure of Airy's Stress Function in Multiply Connected Regions
In solving two-dimensional problems using Airy's stress function for multiply connected regions, the form of the function depends on the dislocations and boundary forces present. The structure of Airy's function is shown to consist of a part expressible in terms of boundary forces and a part expressible in the manner of Poincare. Meanings of the constants occurring in Poincare's expression are discussed.
Date:
July 1951
Creator:
Grioli, Giusippe
System:
The UNT Digital Library
Subsonic Gas Flow Past A Wing Profile
"The use of the linearized equations of Chaplygin to calculate the subsonic flow of a gas permits solving the problem of the flow about a wing profile for absence and presence of circulation. The solution is obtained in a practical convenient form that permits finding all the required magnitudes for the gas flow (lift, lift moment velocity distribution over the profile, and critical Mach number). This solution is not expressed in simple closed form; for a certain simplifying assumption, however, the equations of Chaplygin can be reduced to equations with constant coefficients, and solutions are obtained by using only the mathematical apparatus of the theory of functions of a complex variable" (p. 1).
Date:
July 1950
Creator:
Christianovich, S. A. & Yuriev, I. M.
System:
The UNT Digital Library
Superchargers
"It seems hardly necessary to use a supercharger near sea level simply to mix the gases. The importance of the supercharger will increase with the use of heavy fuels. Before long we shall probably be using two-stroke-cycle and four-stroke-cycle scavenging engines on airplanes. In accord with the present tendency, we shall present here the French solutions of the problem in a practical rather than in a purely theoretical manner" (p. 1).
Date:
July 1931
Creator:
Léglise, Pierre
System:
The UNT Digital Library
Systematic Investigation of Joukowsky Wing Sections
Ackeret began systematic polar measurements on Joukowsky wing sections, which were occasionally conducted in the wind tunnel. Under these conditions a considerable number of wing sections were tested during the last four years and the tests are now more or less concluded.
Date:
July 1927
Creator:
Schrenk, O.
System:
The UNT Digital Library
Technical Progress Shown in the 1927 Rhon Soaring-Flight Contest
Since 1922 the further development of the glider has consisted of a very gradual and arduous improvement in regards to air resistance, weight, strength and maneuverability. This report provides an in-depth examination of these improvements.
Date:
July 1928
Creator:
Hübner, W.
System:
The UNT Digital Library
Test Report on Measurements on a Series of Tapered Wings of Small Aspect Ratio (Trapezoidal Wing with Fuselage)
"This is the second of a series of six reports dealing with three- and six-component measurements on the tapering series at small aspect ratio. The present report concerns the trapezoidal wing with fuselage" (p. 1).
Date:
July 1947
Creator:
Lange & Wacke
System:
The UNT Digital Library
Tests on an Airfoil With Two Slots Suitable for an Aircraft of High Performance: Lift, Drag, Rolling and Yawing Moment Measurements
The results that are described in this article form a complete series of tests on an airfoil fitted with front and rear slots, the rear slot being formed between the portion of the wing aft of the rear spar and the forward portion of the flap.
Date:
July 1926
Creator:
Page, F. Handley
System:
The UNT Digital Library
This Summer's Gliding Meets
This article discusses the upcoming gliding meets in France and Germany in the summer of 1922. Restrictions of design, prize money, and new innovations are all discussed.
Date:
July 1922
Creator:
Warner, Edward P.
System:
The UNT Digital Library
Torsional Rigidity of Cantilever Wings With Constant Spar and Rib Sections
"The present paper treats less of the effect of the union (of spars and ribs, namely, the reduction of the bending moment at the fixed ends of the spars) than of its influence on the torsional rigidity of the wing. The calculations are carried out for a two-spar wing of constant cross section, in which the ribs are replaced by a continuous member of constant rigidity" (p. 1).
Date:
July 1929
Creator:
Gabrielli, Giuseppe
System:
The UNT Digital Library
Towing Tests of Models as an Aid in the Design of Seaplanes
This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
Date:
July 1932
Creator:
Schröder, P.
System:
The UNT Digital Library
The Transport of Vorticity Through Fluids in Turbulent Motion: In the Light of the Prandtl and Taylor Theories
The report studies the problem of the transport of vorticity or of momentum in light of the Taylor and Prandtl theories which are briefly reviewed. It also show how the formulas of Prandtl could be brought into agreement with experimental results in those cases where they agree with the principle of statistic similitude of Karman, and particularly in the problem of the distribution of velocity and temperature in the wake of a heated cylindrical obstacle.
Date:
July 1936
Creator:
Ferrari, C.
System:
The UNT Digital Library
Tunnel Correction for Compressible Subsonic Flow
"This report presents a treatment of the effects of the tunnel walls on the flow velocity and direction in a compressible medium at subsonic speed by an approximate method. Calculations are given for the rotationally symmetric and two-dimensional problems of the flow past bodies, as well for the downwash effect in the tunnel with circular cross section" (p. 1).
Date:
July 1947
Creator:
v. Baranoff, A.
System:
The UNT Digital Library
Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile
"This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle" (p. 1).
Date:
July 1942
Creator:
Keune, F.
System:
The UNT Digital Library
Variable Pitch Propeller
The advantages of variable pitch propellers over constant pitch propellers is presented along with different methods of varying the pitch. The technique of varying the shape of the propeller is presented as the most efficient one.
Date:
July 1923
Creator:
Pistolesi, Enrico
System:
The UNT Digital Library
Velocity and Pressure Distribution Behind Bodies in an Air Current
The following experiments on the air flow behind bodies were made for the purpose of assisting in the explanation of the phenomena connected with air resistance. The first two series of experiments dealt with the phenomena behind a cylinder. The third series of experiments was carried out behind a streamlined strut.
Date:
July 1924
Creator:
Betz, A.
System:
The UNT Digital Library
The Vortex Theory and Its Significance in Aviation
This report will present ideas closely related to the vortex conception and illustrate them in the simplest possible terms. In addition to these general considerations, this report will attempt to show the application of the vortex theory in connection with the wing theory.
Date:
July 1930
Creator:
Betz, A.
System:
The UNT Digital Library