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Application of a high-temperature static strain gage to the measurement of thermal stresses in a turbine stator vane

Description: From Introduction: "This report describes the high-temperature static strain gage and presents the results obtained in a determination of the thermal stresses in a turbine stator vane resulting from the temperature distribution obtained under steady-state conditions at rated speed and temperature of the engine."
Date: March 1958
Creator: Kemp, R H; Morse, C R & Hirschberg, M H

The application of a simplified lifting-surface theory to the prediction of the rolling effectiveness of plain spoiler ailerons at subsonic speeds

Description: From Introduction: "It is the purpose to describe a method of predicting spoiler rolling-moment effectiveness based on the simplified lifting-surface flap theory of reference 12. The results of applying the present method to the configurations described in references 1 to 8 (see table I and fig. 1) and the comparison with the experimental data are presented herein."
Date: December 6, 1954
Creator: Franks, Ralph W

Application of a windshield-display system to the low-altitude bombing problem

Description: From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."
Date: January 4, 1957
Creator: Barnett, Robert M; Kaufman, William M & Fulcher, Elmer C

The application of the statistical theory of extreme values to gust-load problems

Description: From Introduction: "Recent developments in the statistical theory of extreme values (references 4 to 10) have indicated a somewhat more rational approach to the problem of predicting the probability of occurrence The present report summarizes some of these findings, indicates the method of application, and evaluates their applicability to certain gust-load problems ."
Date: July 22, 1949
Creator: Press, Harry

The 1929 Rhon soaring-flight contest

Description: The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
Date: April 1930
Creator: Lippisch, Alexander

Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil

Description: This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both in the laboratory and in flight show conclusively that it is necessary to heat only the front portion of the wing surface to effect complete prevention. Experiments in flight show that a vapor-heating system which extracts heat from the exhaust and distributes it to the wings is an entirely practical and efficient method for preventing ice formation.
Date: January 1, 1933
Creator: Clay, William C & Theodorsen, Theodore

Airfoil Theory at Supersonic Speed

Description: A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 1918-1919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the drag-lift ratio is considerably less favorable than is the case for incompressible flow. Among others the following examples are considered: 1) lifting line with constant lift distribution (horseshoe vortex); 2) computation of wave and induced drag and the twist of a trapezoidal wing of constant lift density; 3) computation of the lift distribution and drag of an untwisted rectangular wing.
Date: June 1939
Creator: Schlichting, H

Experimental investigation of the physical properties of medium and heavy oils, their vaporization and use in explosion engines. Part IV

Description: This report presents a theoretical treatment of the vaporization process of medium and heavy oils. The results of this investigation, which were mostly obtained from the lighter components of the heavy fuels, require a 10- or 16-fold vaporization in comparison with gasoline. We must attain a still finer degree of atomization, in order to include the heavier components.
Date: December 1926
Creator: Heinlein, Fritz

Twelfth Rhon soaring contest, 1931

Description: 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.
Date: May 1932
Creator: Georgii, Walter

Airplane drag

Description: It has been less well understood that the induced drag (or, better said, the undesired increase in the induced drag as compared with the theoretical minimum calculated by Prandtl) plays a decisive role in the process of taking off and therefore in the requisite engine power. This paper seeks to clarify the induced drag.
Date: December 1929
Creator: Topfer, Carl

Airplane flight in the stratosphere

Description: This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Date: February 1932
Creator: De Caria, Ugo

Aeronautical education and research at the Swiss Institute of Technology in Zurich

Description: Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
Date: April 1931
Creator: Karner, L & Ackeret, J

The dangerous sideslip of a stalled airplane and its prevention

Description: This investigation covers only that phase of airplane accidents which are the result of sideslip. We examine the circumstances under which this occurs, study the behavior of present-day airplane types (monoplane, conventional and staggered biplane) therein and endeavor to find a solution whereby this danger may be avoided.
Date: September 1, 1931
Creator: Schmidt, Wilhelm & Fuchs, Richard

Mathematical treatise on the recovery from a flat spin

Description: In this mathematical investigation, made in collaboration with Dr. Wilhelm Schmidt, we interpret the temporary change (due to some disturbance) in the quantities which define the position of the airplane while in a flat spin. We further examine the effect of this change, of the means resorted to to produce the disturbance, and thus reveal the expedients available for recovering from a flat spin.
Date: November 1930
Creator: Fuchs, R