UNT Libraries Government Documents Department - 79 Matching Results

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A Ram-Jet Engine for Fighters

Description: Simple and accurate calculations are made of the flow process in a continuous compressorless Lorin jet-propulsion unit. Experimental confirmation is given from towing tests on an airplane at flying speeds up to 200 miles per second. An analysis is made of the performance of a fighter-type airplane designed for utilization of this propulsion system.
Date: October 1947
Creator: Sänger, E. & Bredt, I.
Item Type: Refine your search to only Report
open access

Force and Pressure-Distribution Measurements on a Rectangular Wing With a Slotted Droop Nose and With Either Plain and Split Flaps in Combination or a Slotted Flap

Description: Force measurements and pressure distribution measurements on the midsection were made on a rectangular wing with slotted droop nose and end plates, on which could be placed a choice of either a plain flap-split flap combination or a slotted flap.
Date: March 1947
Creator: Lemme, H. G.
Item Type: Refine your search to only Report
open access

Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers)

Description: "The problem of the intake of air is treated for a missile flying at supersonic speeds and of changing the kinetic energy of the air into pressure with the least possible losses. Calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values… more
Date: June 1947
Creator: Oswatitsch, K.
Item Type: Refine your search to only Report
open access

The Load Distribution in Bolted or Riveted Joints in Light-Alloy Structures

Description: "This report contains a theoretical discussion of the load distribution in bolted or riveted joints in light-alloy structures which is applicable not only for loads below the limit of proportionality but also for loads above this limit. The theory is developed for double and single shear joints. The methods given are illustrated by numerical examples and the values assumed for the bolt (or rivet) stiffnesses are based partly on theory and partly on known experimental values" (p. 1).
Date: April 1947
Creator: Vogt, F.
Item Type: Refine your search to only Report
open access

Gas-Dynamic Investigations of the Pulse-Jet Tube, Parts 1 and 2

Description: Based upon a simplified representation of the mode of operation of the pulse-jet tube, the effect of the influences mentioned in the title were investigated and it will be shown that, for a jet tube with a form designed to be aerodynamically favorable, the ability to operate is at least questionable. This investigation will account for the important practical observation made by Paul Schmidt that the ratio of the effective valve cross-sectional area to the tube cross section may not be of any r… more
Date: February 1947
Creator: Schultz-Grunow, F.
Item Type: Refine your search to only Report
open access

The Effect of Turbulence on the Flame Velocity in Gas Mixtures

Description: "The present report deals with the effect of turbulence on the propagation of the flame. Being based upon experiments with laminar as well as turbulent Bunsen flames, both the physico-chemical and the hydro-dynamical aspects of the problem are analyzed. A number of new deductions, interesting from the point of view of engine combustion and other very rapidly changing flame reactions, are made" (p. 1).
Date: April 1947
Creator: Damköhler, Gerhard
Item Type: Refine your search to only Report
open access

Pressure Distribution Measurements at High Speed and Oblique Incidence of Flow

Description: "The present report contains the results of a series of observations obtained for a wing of symmetrical profile for different angles of yaw. The shock tunnel with 0.4m x 0.4m cross section, of the Institute for Gas Dynamics at L.F.A. - Braunchweig was available for this work. The profile used was a 9 percent, thick hyperbolic profile with maximum thickness 40 percent aft, which was calculated by the method of F. Ringleb (2). Since the conformal transformation of this profile is known, the theor… more
Date: March 1947
Creator: Lippisch, A. & Beuschausen, W.
Item Type: Refine your search to only Report
open access

The Elasto-Plastic Stability of Plates

Description: This article explains results developed from the following research: 'The Stability of Plates and Shells beyond the Elastic Limit.' A significant improvement is found in the derivation of the relations between the stress factors and the strains resulting from the instability of plates and shells. In a strict analysis, the problem reduces to the solution of two simultaneous nonlinear partial differential equations of the fourth order in the deflection and stress function, and in the approximate … more
Date: December 1947
Creator: Ilyushin, A. A.
Item Type: Refine your search to only Report
open access

The Lift Distribution of Swept-Back Wings

Description: "Two procedures for calculating the lift distribution along the span are given in which a better account is taken of the distribution of circulation over the area than in the Prandtl lifting-line theory. The methods are also applicable to wing sweepback. Calculated results for the two methods were in agreement" (p. 1).
Date: March 1947
Creator: Weissinger, J.
Item Type: Refine your search to only Report
open access

Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Date: January 1947
Creator: Ackeret, J.; Feldmann, F. & Rott, N.
Item Type: Refine your search to only Report
open access

Infinitesimal Conical Supersonic Flow

Description: The calculation of infinitesimal conical supersonic flow has been applied first to the simplest examples that have also been calculated in another way. Except for the discovery of a miscalculation in an older report, there was found the expected conformity. The new method of calculation is limited more definitely to the conical case.
Date: March 1947
Creator: Busemann, Adolf
Item Type: Refine your search to only Report
open access

Investigations on Experimental Impellers for Axial Blowers

Description: "A selection of measurements obtained on experimental impellers for axial blowers will be reported. In addition to characteristic curves plotted for low and for high peripheral velocities, proportions and blade sections for six different blower models and remarks on the design of blowers will be presented" (p. 1).
Date: April 1947
Creator: Encke, W.
Item Type: Refine your search to only Report
open access

Possibilities of Reducing the Length of Axial Superchargers for Aircraft Motors

Description: Axial blowers are gaining importance as aircraft engine superchargers. However, the pressure head obtainable per stage is small. Due to the necessary great number of stages, the physical length of the blower becomes too great for an airworthy device. This report discusses several types of construction that permit a reduction in the length of the blower.
Date: January 1947
Creator: Eckert, B.
Item Type: Refine your search to only Report
open access

Drag Corrections in High-Speed Wind Tunnels

Description: In the vicinity of a body in a wind tunnel the displacement effect of the wake, due to the finite dimensions of the stream, produces a pressure gradient which evokes a change of drag. In incompressible flow this change of drag is so small, in general, that one does not have to take it into account in wind-tunnel measurements; however, in compressible flow it beoomes considerably larger, so that a correction factor is necessary for measured values. Correction factors for a closed tunnel and an o… more
Date: July 1947
Creator: Ludwieg, H.
Item Type: Refine your search to only Report
open access

Preliminary Report on the Fundamentals of the Control of Turbine-Propeller Jet Power Plant

Description: "On the basis of the investigations so far completed on the behavior of PTL power plants under various operating conditions, in which the influence of the propeller characteristics is of considerable importance, the most important aspects of a control system for turbine-propeller jet power plants are deduced. A simple possible means for its concrete realization, which is also applicable to TL [NACA comment: TL, jet] power plants, is presented by means of examples. A control device of this kind … more
Date: July 1947
Creator: Kühl, H.
Item Type: Refine your search to only Report
open access

Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers

Description: "With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method" (p. 1).
Date: July 1947
Creator: Regenscheit, B.
Item Type: Refine your search to only Report
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