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Technical report of the 1928 Rhon soaring-flight contest
Report presenting some information on the gliders that participated in the 1928 Rhön soaring flight contest. Almost all of the gliders represented an improvement over gliders used in the previous years. A great increase in the skill of the glider pilots is also noted.
Date:
May 1929
Creator:
Lippisch, A.
System:
The UNT Digital Library
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Trapezoidal Wing)
The present report, which forms the first of six articles on experiments with airfoils of aspect ratio from 1 to 3 and various planforms, deals with the three- and six-component measurements made on the trapezoidal wing series in the 2.15 x 3-meter wind tunnel of the DVL at the request of the Henschel Aircraft Company.
Date:
May 1949
Creator:
Lange & Wacke
System:
The UNT Digital Library
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Triangular Wing)
The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
Date:
May 1948
Creator:
Lange & Wacke
System:
The UNT Digital Library
Torsional Stresses in Box Beams With Cross Sections Partially Restrained Against Warping
"The present report gives a method for computing the torsion of boxes with thin shear-resistant or simply tension-resistant walls under any torsional load, support and dimension. The final stress condition is developed from that of a principal system with unconstrained sectional warping corresponding to Bredt's formula and an additional stress condition due to constrained cross-sectional warping. This is computed by means of the deflection condition of the principal system from a statically indeterminate calculation" (p. 1).
Date:
May 1934
Creator:
Ebner, Hans
System:
The UNT Digital Library
Torsional Vibration of Aircraft Engines
"Exhaustive torsional-vibration investigations are required to determine the reliability of aircraft engines. A general outline of the methods used for such investigations and of the theoretical and mechanical means now available for this purpose is given, illustrated by example. True vibration diagrams are usually obtained from vibration measurements on the completed engine. Two devices for this purpose and supplementing each other, the D.V.L. torsiograph and the D.V.L. torsion recorder, are described in this report" (p. 1).
Date:
May 1932
Creator:
Lürenbaum, Karl
System:
The UNT Digital Library
Twelfth Rhon Soaring Contest, 1931
The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated. A description of some of the aircraft present at the event is provided.
Date:
May 1932
Creator:
Georgii, Walter
System:
The UNT Digital Library
Ultra-Light Alloys and Their Utilization on Aircraft
Memorandum presenting an overview of ultra-light alloys and their potential use on an aircraft. A definition of ultra-light alloys, some of the present possibilities of ultra-light alloys, and some of the principles governing the use of the alloys in aircraft are provided.
Date:
May 1924
Creator:
Portevin, A. M. & DeFleury, R.
System:
The UNT Digital Library
Wall Interference in a Perforated Wind Tunnel
"The theory of cascades, made up of a series of flat plates placed one behind the other, is extended to the case where the impinging stream is not uniform, and the deduced properties of this cascade-flow are then applied to the study of the wall interference between such as cascade-like boundary and a vortex-source type of singularity. It is shown that the induced velocities, produced by the presence of such a wall, are equal to what is obtained by action of a suitably chosen 'reflected' singularity situated on one side of the wall, together with the action of another suitably chosen 'transmitted' singularity placed on the other side" (p. 1).
Date:
May 1957
Creator:
Brescia, Riccardo
System:
The UNT Digital Library
The Way to Increased Airplane Engine Power
The purpose of this paper is to give an outline of the present state of development and point out the possibilities available for the further increase in the power/displacement ratio, the economy, and the reliability of the engine. Some of the aspects discussed are methods of increasing take-off power, the various methods of preparation of the fuel mixture and their effect on power, economy, and safety.
Date:
May 1939
Creator:
Vohrer, Eugen
System:
The UNT Digital Library
Wheel Brakes and Their Application to Aircraft
"The advantages to be gained from braking have not been ignored, and in the search for a suitable method many schemes have been suggested and tried. Some of the methods discussed in this paper include: 1) increasing the height of the landing gear; 2) air brakes of various forms; 3) sprags on tail skid and axle; and 4) wheel brakes. This report focuses on the design of wheel brakes and wheel brake controls" (p. 1).
Date:
May 1928
Creator:
Dowty, G. H.
System:
The UNT Digital Library
Wind Tunnel Tests of Correction Formula for Wings of Large Span
The theory (wing experiments in an artificial air stream are subject to error, due to the fact that the wing is not situated in an unlimited body of air) by means of which the given drag correction was obtained, was based on various assumptions (e.g., elliptical distribution of lift) which do not always hold true. For this reason it was desirable to test the equation for the additional drag in regard to its reliability and range of application.
Date:
May 1924
Creator:
Wieselsberger, C.
System:
The UNT Digital Library
Wind-Tunnel Tests on Various Types of Dive Brakes Mounted in Proximity of the Leading Edge of the Wing
"The present report is concerned with a series of tests on a model airplane fitted with four types of dive flaps of various shapes, positions, and incidence located near the leading edge of the wing (from 5 to 20 percent of the wing chord). Tests were also made on a stub airfoil fitted with a ventral dive (located at 8 percent of the wing chord). The hinge moments of the dive flaps were measured" (p. 1).
Date:
May 1949
Creator:
Lattanzi, Bernardino & Bellante, Erno
System:
The UNT Digital Library