Technical Report Archive & Image Library (TRAIL) - 380 Matching Results

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Development of the Junkers-Diesel Aircraft Engine

Description: The working process of the Junkers engine has resulted from a series of attempts to attain high performance and to control the necessarily rapid and complete combustion at extremely high speeds. The two main problems of Diesel engines in aircraft are addressed; namely, incomplete combustion and the greater weight of Diesel engine parts compared to gasoline engines.
Date: May 1930
Creator: Gasterstädt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of the Rules Governing the Strength of Airplanes Part 1: German Loading Conditions Up to 1926

Description: Load factors and loading conditions are presented for German aircraft. Loading conditions under various stress factors are presented along with a breakdown of individual aircraft components such as landing gear, wings, etc.
Date: July 1933
Creator: Küssner, H. G. & Thalau, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of the Rules Governing the Strength of Airplanes Part 2: Loading Conditions in Germany (Continued), England and the United States

Description: Load factors and loading conditions are presented for Germany, England, and the United States. Results of tests are presented and loading conditions are presented under various stress categories like freight, commercial, aerobatics, and training.
Date: July 1933
Creator: Küssner, H. G. & Thalau, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of the Rules Governing the Strength of Airplanes Part 3: Loading Conditions in France, Italy, Holland, and Russia - Aims at Standardization

Description: The historical development of the rules for structural strength of aircraft in the leading countries is traced from the beginning of flight to date. The term "factor of safety" is critically analyzed; its replacement by probability considerations has been considered desirable.
Date: August 1933
Creator: Küssner, H. G. & Thalau, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Discussion of the Several Types of Two-Stroke-Cycle Engines

Description: This report discusses different types of two-stroke engines as well as the three most important design factors: volume of scavenge and charge delivery, scavenging process (scavenging result), and result of charge. Some of the types of engines discussed include: single cylinder with crank-chamber scavenge pump and auxiliary suction piston linked to working connecting rod; and two cylinder engines with a rotary scavenge pump arrangement. Three and four cylinder engines are also discussed in vario… more
Date: September 1935
Creator: Venediger, Herbert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Disintegration of a Liquid Jet

Description: This report presents an experimental determination of the process of disintegration and atomization in its simplest form, and the influence of the physical properties of the liquid to be atomized on the disintegration of the jet. Particular attention was paid to the investigation of the process of atomization.
Date: February 1932
Creator: Haenlein, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Distribution of Temperatures Over an Airplane Wing With Reference to the Phenomena of Ice Formation

Description: The results obtained from the present study of temperature distribution over an airplane wing afford means for making the following statements as regards the conditions of ice accretion and the use of a thermic anti-icer or de-icer: 1) Ice can form on a wing only when the temperature is below or hovering around zero. 2) The thermic effects produced on contact of the air with the moving wing rather oppose ice accretion. 3) The thermic procedure in the fight against ice accretion on the wing cons… more
Date: December 1938
Creator: Brun, Edmond
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Dornier wind tunnel

Description: After completion of the required calibrations, the Dornier open-throat tunnel is now in operation. With an elliptic test section of 3 by 4 m (9.84 by 3.12 ft.), its length is 7 m (22.97 ft.), its maximum horsepower 800, and its maximum air speed 60 m/s (134.2 mph). As to local uniformity of velocity, static pressure as well as jet direction, and turbulence factor, this tunnel is on par with those of the good German and foreign research labs.
Date: June 1938
Creator: Schlichting, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Downwash Measurements Behind Wings With Detached Flow

Description: This investigation, which was made in the small wind tunnel having a diameter of 1.2 m (3.94 feet), embraced three wing models, behind which, at various angles of attack between 0 and 60 degrees, the static pressure and the total pressure along vertical lines (perpendicular to the direction of the undisturbed wind and to the wing span) were measured. The location of these vertical lines are indicated in Figure 1. Moreover, the wing polars were determined by the customary three-component measure… more
Date: August 1931
Creator: Petersohn, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Drag of Airplane Radiators With Special Reference to Air Heating (Comparison of Theory and Experiment)

Description: This report contains a survey of past radiator research. This report also is intended as a systematic comparison of theoretical and experimental radiator drag, with the object of ascertaining the most important loss sources and their interaction in different cases of installation, and to separate the radiator systems which are amenable to calculation, both as regards axial flow and drag. The sources of loss due to the diffuser are to be looked into closely as in many cases they can be of preemi… more
Date: May 1939
Creator: Göthert, B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Breaking Tests of Airplane Parts

Description: "The static stresses of airplane parts, the magnitude of which can be determined with the aid of static load assumptions, are mostly superposed by dynamic stresses, the magnitude of which has been but little explored. The object of the present investigation is to show how the strength of airplane parts can best be tested with respect to dynamic stresses with and without superposed static loading, and to what extent the dynamic strength of the parts depends on their structural design. Experiment… more
Date: January 1933
Creator: Hertel, Heinrich
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Stability of a Helicopter With Hinged Rotor Blades

Description: "The present report is a study of the dynamic stability of a helicopter with hinged rotor blades under hovering conditions. While in this case perfect stability can in general not be obtained it is possible by means of design features to prolong the period of the spontaneous oscillations of the helicopter and reduce their amplification, and so approximately assure neutral equilibrium. The possibility of controlled stability of a helicopter fitted with hinged blades is proved by the successful f… more
Date: September 1939
Creator: Hohenemser, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Testing of Airplane Shock-Absorbing Struts

Description: "Measurement of perpendicular impacts of a landing gear with different shock-absorbing struts against the drum testing stand. Tests were made with pneumatic shock absorbers having various degrees of damping, liquid shock absorbers, steel-spring shock absorbers and rigid struts. Falling tests and rolling tests. Maximum impact and gradual reduction of the impacts in number and time in the falling tests. Maximum impact and number of weaker impacts in rolling tests" (p. 1).
Date: January 1932
Creator: Langer, P. & Thomé, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of a Gap Between Elevator and Stabilizer on the Static Stability and Maneuverability About the Lateral Axis in Flight

Description: "A number of German airplanes have a gap between elevator and stabilizer. The effect of this open space is not generally known, although English wind-tunnel experiments have shown that even a very small gap exerts a profound influence on the elevator action. The purpose of the present free-flight measurements is to ascertain whether fairing over the gap would actually result in an appreciable improvement" (p. 1).
Date: March 1933
Creator: Hübner, Walter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of aerodynamic design on glider performance

Description: The performance of a glider is determined by means of the velocity polar, which represents the connection between horizontal and sinking speed. The mean sinking speed for a given speed range can be determined on the basis of the velocity polar. These data form the basis for the most propitious design of a performance-type glider with a view to long-distance flight.
Date: January 1935
Creator: Lippisch, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Air-Fuel Ratio on Detonation in Gasoline Engines

Description: Memorandum presenting a study of the effect of mixture strength on detonation, which may be divided into two parts, namely: a) the measurement of the effect in engines; and b) the explanation of the effect. This is because of the richness of the mixture has a very pronounced effect on the detonation in a gasoline engine.
Date: March 1938
Creator: Peletier, L. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Compressibility on the Pressure Reading of a Prandtl Pitot Tube at Subsonic Flow Velocity

Description: Errors arising from yawed flow were also determined up to 20 degrees angle of attack. In axial flow, the Prandtl pitot tube begins at w/a approx. = 0.8 to give an incorrect static pressure reading, while it records the tank pressure correctly, as anticipated, up to sonic velocity. Owing to the compressibility of the air, the Prandtl pitot tube manifests compression shocks when the air speed approaches velocity of sound. This affects the pressure reading of the instrument. Because of the increas… more
Date: November 1939
Creator: Walchner, O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Fuselage and Engine Nacelles on Some Aerodynamic Properties of an Airplane Wing

Description: "With the aid of the method of J. Lotz, the writer undertook to solve theoretically the lift distribution along the span of an airplane wing, when the outline of the wing is uneven. This problem arises in the case of a mid-wing monoplane with embedded engine nacelles. The fuselage and the nacelles were considered as aerodynamically profiled, that is, as lift-producing parts. The task was therefore to determine not only the disturbance caused by the fuselage and nacelles, but also their share in… more
Date: February 1934
Creator: Vladea, Joan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of propeller slipstream on wing and tail

Description: The results of wind tunnel tests for the determination of the effect of a jet on the lift and downwash of a wing are presented in this report. In the first part, a jet without rotation and with constant velocity distribution is considered - the jet being produced by a specially designed fan. Three-component, pressure distribution, and downwash measurements were made and the results compared with existing theory. The effect of a propeller slipstream was investigated in the second part. In the tw… more
Date: August 1938
Creator: Stüper, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Stabilizing Forces on Turbulence

Description: The appearance of expressed discontinuity layers in the free atmosphere, where a warm air mass flows over a cold mass without perceptible intermingling forms the basis of the present report. In these experiments an air stream is to be blown between a water-cooled and a vapor-heated plate. According to what preceded it is anticipated that the exchange will be enhanced.
Date: June 1931
Creator: Prandtl, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of the Ground on an Airplane Flying Close to It

Description: In America and England the ground effect has received much attention for a long time, and whole series of model and flight tests have been made, which have, however, been chiefly devoted to changes in the induced drag. The experiments here described show that the increase in lift may be of high enough order of magnitude to be taken into account also.
Date: June 1932
Creator: Tönnies, E
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of the Masses of the Controls on the Longitudinal Stability With Free Elevator Part 1

Description: In the present report, aerodynamic relations under the effect of the weight moments are investigated, and an example given of the computation of the stability for a practical case. Later, the effects of the masses of the controls on the dynamic longitudinal stability will be considered.
Date: July 1939
Creator: Schmidt, Rudolf
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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