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The 5- by 7-meter wind tunnel of the DVL
The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Date:
March 1936
Creator:
Kramer, M.
System:
The UNT Digital Library
The 1926 German Seaplane Contest
The report discusses the problem of rating the various seaplane designs from the 1926 seaplane contest. The whole process of rating consists in measuring the climbing speed, flying weight and carrying capacity of a seaplane and then using these data as the basis of a construction problem.
Date:
March 1928
Creator:
Seewald, F.; Blenk, H. & Liebers, F.
System:
The UNT Digital Library
Abacus Giving the Variation of the Mean Pressure of an Aviation Engine as a Function of its Speed of Rotation
Comparing the results of the calculations for computing the mean pressure of an aviation engine for any number of revolutions, with those of experiment, the writer, by numerous examples, shows the perfect agreement between them. This report will show that, by means of a special abacus, an engineer can instantly plot the characteristics of an engine.
Date:
March 1921
Creator:
Margoulis, W.
System:
The UNT Digital Library
Accurate Calculation of Multispar Cantilever and Semicantilever Wings With Parallel Webs Under Direct and Indirect Loading
In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Date:
March 1932
Creator:
Sänger, Eugen
System:
The UNT Digital Library
Aeronautic Insurance
The problem of insuring the emerging commercial aeronautic industry is detailed. The author also motes that a complete solution cannot be obtained until the necessary statistics are compiled.
Date:
March 1922
Creator:
Neal, Erik
System:
The UNT Digital Library
The Aeronautical Laboratory of the Stockholm Technical Institute
This report presents a detailed analysis and history of the construction and operation of the aeronautical laboratory of the Stockholm Technical Institute. Engines and balances are discussed and experimental results are also given.
Date:
March 1935
Creator:
Malmer, Ivar
System:
The UNT Digital Library
Altitude of equilibrium of an airship
This report details the procedure followed in establishing a general formula enabling the calculation of the maximum altitude attainable statically.
Date:
March 1925
Creator:
Nobile, Umberto
System:
The UNT Digital Library
Analysis of Experimental Investigations of the Planing Process of the Surface of Water
Pressure distribution and spray measurements were carried out on rectangular flat and V-bottom planing surfaces. Lift, resistance, and center of pressure data are analyzed and it is shown how these values may be computed for the pure planing procees of a flat or V-bottom suface of arbitrary beam, load and speed, the method being illustrated with the aid of an example.
Date:
March 1944
Creator:
Sottorf, W.
System:
The UNT Digital Library
Analysis of flight and wind-tunnel tests on Udet airplanes with reference to spinning characteristics
This report presents an analysis of results of wind-tunnel tests conducted at the D.V.L. Values were determined for the effectiveness of all the controls at various angles of attack. The autorotation was studied by subjecting the rotating model to an air blast.
Date:
March 1929
Creator:
Herrmann, H.
System:
The UNT Digital Library
Analytical methods for computing the polar curves of airplanes
This report presents a method of calculating polar curves which is at least as precise as graphical methods, but it more rapid. Knowing the wind tunnel test of a wing and the performances of an airplane of the same profile, it is easy to verify the characteristic coefficients and, at the same time, the methods determining induced resistances.
Date:
March 1921
Creator:
Le Sueur
System:
The UNT Digital Library
Analytical Theory of the Campini Propulsion System
"The present report deals exclusively with the particular jet-propulsion system mentioned in the cited reports. The discussion is limited, for the present, to the analytical study of the efficiency and the consumption for the case of application to aircraft and to the plotting of the practical operating curves secured theoretically by the use of suitable experimental factors" (p. 1).
Date:
March 1942
Creator:
Campini, S.
System:
The UNT Digital Library
Application of the Methods of Gas Dynamics to Water Flows With Free Surface 1: Flows With No Energy Dissipation
The application is treated in sufficient detail to facilitate as much as possible its application by the engineer who is less familiar with the subject. The present work was undertaken with two objects in view. In the first place, it is considered as a contribution to the water analogy of gas flows, and secondly, a large portion is devoted to the general theory of the two-dimensional supersonic flows.
Date:
March 1940
Creator:
Preiswerk, Ernst
System:
The UNT Digital Library
Application of the Methods of Gas Dynamics to Water Flows With Free Surface 2: Flows With Momentum Discontinuities (Hydraulic Jumps)
In this paper an introduction to shock polar diagrams is given which then leads into an examination of water depths in hydraulic jumps. Energy loss during these jumps is considered along with an extended look at elementary solutions of flow. An experimental test set-up is described and the results presented.
Date:
March 1940
Creator:
Preiswerk, Ernst
System:
The UNT Digital Library
An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape
From Summary: "Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account."
Date:
March 1949
Creator:
Schlichting, H.
System:
The UNT Digital Library
The Art of Writing Scientific Reports
As the purpose of the report is to transmit as smoothly and as easily as possible, certain facts and ideas, to the average person likely to read it, it should be written in a full and simple enough manner to be comprehended by the least tutored, and still not be boring to the more learned readers.
Date:
March 1921
Creator:
Norton, F. H.
System:
The UNT Digital Library
Atmospheric Waves and Their Utilization in Soaring Flight
In soaring flight, ascending air currents are utilized and the interesting question is raised whether there are such currents which extend to any considerable distance and which can be utilized practically.
Date:
March 1923
Creator:
Baldit, M. Albert
System:
The UNT Digital Library
Bagnulo Heavy Fuel Internal Combustion Engine and Its Employment in Aviation
We see with great satisfaction that Bagnulo's studies and experiments on his high-speed, heavy-fuel engines, promise to solve not only the general problem of economical power and hence of thermal efficiency, but also all other special problems, of weight and space, and, what is still more important, range of error.
Date:
March 1922
Creator:
Fiore, Amedeo
System:
The UNT Digital Library
The Bending of Beams With Thin Tension Flanges
This report analyzes the action of a cantilever T beam with a tension flange so thin it can only carry tensile stresses.
Date:
March 1935
Creator:
Cicala, Placido
System:
The UNT Digital Library
The Boundary Layer as a Means of Controlling the Flow of Liquids and Gases
According to one of the main propositions of the boundary layer theory the scarcely noticeable boundary layer may, under certain conditions, have a decisive influence on the form of the external flow by causing it to separate from the wing surface. These phenomena are known to be caused by a kind of stagnation of the boundary layer at the point of separation. The present report deals with similar phenomena. It is important to note that usually the cause (external interference) directly affects only the layer close to the wall, while its indirect effect extends to a large portion of the external flow.
Date:
March 1930
Creator:
Schrenk, Oskar
System:
The UNT Digital Library
Calculation of Airplane Performances Without the Aid of Polar Diagrams
For good profiles the profile-drag coefficient is almost constant in the whole range which comes into consideration for practical flight. This is manifest in the consideration of the Gottingen airfoil tests and is confirmed by the investigations of the writer (measurements of the profile drag during flight by the Betz method), concerning which a detailed report will soon be published. The following deductions proceed from this fact. The formulas developed on the assumptions of a constant profile-drag coefficient afford an extensive insight into the influences exerted on flight performances by the structure of the airplane.
Date:
March 1928
Creator:
Schrenk, Martin
System:
The UNT Digital Library
The Calculation of Compressible Flows with Local Regions of Supersonic Velocity
This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
Date:
March 1947
Creator:
Göthert, B. & Kawalki, K. H.
System:
The UNT Digital Library
Calculation of Counterrotating Propellers
"A method for calculation of a counterrotating propeller which is similar to Walchner's method for calculation of the single propeller in the free air stream is developed and compared with measurements. Several dimensions which are important for the design are given end simple formulas for the gain in efficiency derived. Finally a survey of the behavior of the propeller for various operating conditions is presented" (p. 1).
Date:
March 1949
Creator:
Ginzel, F.
System:
The UNT Digital Library
Calculation of the Bending Stresses in Helicopter Rotor Blades
A comparatively rapid method is presented for determining theoretically the bending stresses of helicopter rotor blades in forward flight. The method is based on the analysis of the properties of a vibrating beam, and its uniqueness lies in the simple solution of the differential equation which governs the motion of the bent blades.
Date:
March 1951
Creator:
de Guillenchmidt, P.
System:
The UNT Digital Library
Calculation of Wing Spars of Variable Cross-Section and Linear Load
"The calculation of wing spars of constant cross-section and load has been thoroughly treated by a large number of authors. Such is not the case,however, regarding the calculation of wing spars whose section and linear load diminish toward the ends, as in wings of trapezoidal contour and decreasing section" (p. 1).
Date:
March 1925
Creator:
Kirste, Léon
System:
The UNT Digital Library