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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Computation of Thin-Walled Prismatic Shells

Computation of Thin-Walled Prismatic Shells

Date: January 1, 1949
Creator: Vlasov, V. Z.
Description: We consider a prismatic shell consisting of a finite number of narrow rectangular plates and having in the cross-section a finite number of closed contours (fig. 1(a)). We shall assume that the rectangular plates composing the shell are rigidly joined so that there is no motion of any kind of one plate relative to the others meeting at a given connecting line. The position of a point on the middle prismatic surface is considered to be defined by the coordinate z, the distance to a certain initial cross-section z = O, end the coordinate s determining its position on the contour of the cross-section.
Contributing Partner: UNT Libraries Government Documents Department
A study of the radiation from laminar and turbulent open propane-air flames as a function of flame area, equivalence ratio, and fuel flow rate

A study of the radiation from laminar and turbulent open propane-air flames as a function of flame area, equivalence ratio, and fuel flow rate

Date: August 24, 1954
Creator: Clark, Thomas P & Bittker, David A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Performance of a Jet Power Plant, III, operating characteristics of a jet power plant as a function of altitude

Flight Performance of a Jet Power Plant, III, operating characteristics of a jet power plant as a function of altitude

Date: May 1, 1951
Creator: Weinig, F.
Description: The performance of a jet power plant consisting of a compressor and a turbine is determined by the characteristic curves of these component parts and is controllable by the characteristics of the compressor and the turbine i n relation t o each other. The normal. output, overload, and throttled load of the Jet power plant are obtained on the basis of assumed straight-line characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

Date: December 3, 1946
Creator: Jarvis, George A. & Cederborg, Gibson A.
Description: A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult. The performance of the model was determined by making visual observations, by recording lengths of run and time histories of decelerations, and by taking motion pictures of the ditchings.
Contributing Partner: UNT Libraries Government Documents Department
Rocket-model investigation to determine the lift and pitching effectiveness of small pulse rockets exhausted from the fuselage over the surface of an adjacent wing at Mach numbers from 0.9 to 1.8

Rocket-model investigation to determine the lift and pitching effectiveness of small pulse rockets exhausted from the fuselage over the surface of an adjacent wing at Mach numbers from 0.9 to 1.8

Date: September 30, 1958
Creator: Martz, C William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer of Airfoils and Plates

Heat Transfer of Airfoils and Plates

Date: April 1, 1943
Creator: Seibert, Otto
Description: The few available test data on the heat dissipation of wholly or partly heated airfoil models are compared with the corresponding data for the flat plate as obtained by an extension of Prandtl's momentum theory, with differentiation between laminar and turbulent boundary layer and transitional region between both, the extent and appearance of which depend upon certain critical factors. The satisfactory agreement obtained justifies far-reaching conclusions in respect to other profile forms and arrangements of heated surface areas. The temperature relationship of the material quantities in its effect on the heat dissipation is discussed as far as is possible at tk.e present state of research, and it is shown that the profile drag of heated wing surfaces can increase or decrease with the temperature increase depending upon the momentarily existent structure of the boundary layer.
Contributing Partner: UNT Libraries Government Documents Department
Researches on Preliminary Chemical Reactions in Spark-Ignition Engines

Researches on Preliminary Chemical Reactions in Spark-Ignition Engines

Date: June 1, 1943
Creator: Muehlner, E.
Description: Chemical reactions can demonstrably occur in a fuel-air mixture compressed in the working cylinder of an Otto-cycle (spark ignition) internal-combustion engine even before the charge is ignited by the flame proceeding from the sparking plug. These are the so-called "prelinminary reactions" ("pre-flame" combustion or oxidation), and an exact knowledge of their characteristic development is of great importance for a correct appreciation of the phenomena of engine-knock (detonation), and consequently for its avoidance. Such reactions can be studied either in a working engine cylinder or in a combustion bomb. The first method necessitates a complicated experimental technique, while the second has the disadvantage of enabling only a single reaction to be studied at one time. Consequently, a new series of experiments was inaugurated, conducted in a motored (externally-driven) experimental engine of mixture-compression type, without ignition, the resulting preliminary reactions being detectable and measurable thermometrically.
Contributing Partner: UNT Libraries Government Documents Department
Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Date: September 17, 1958
Creator: Coltrane, Lucille C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The "Junkers-Junior" Light Airplane (German) : A Two-Seat All-Metal Low-Wing Cantilever Monoplane

The "Junkers-Junior" Light Airplane (German) : A Two-Seat All-Metal Low-Wing Cantilever Monoplane

Date: June 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Turbine Axial Nozzle-Wheel Clearance on Performance of Mark 25 Torpedo Power Plant

Effect of Turbine Axial Nozzle-Wheel Clearance on Performance of Mark 25 Torpedo Power Plant

Date: January 1, 1948
Creator: Hoyt, Jack W. & Kottas, Harry
Description: Investigations were made of the turbine from a Mark 25 torpedo to determine the performance of the unit with three different turbine nozzles at various axial nozzle-wheel clearances. Turbine efficiency with a reamed nondivergent nozzle that uses the axial clearance space for gas expansion was little affected by increasing the axial running clearance from 0.030 to 0.150 inch. Turbine efficiency with cast nozzles that expanded the gas inside the nozzle passage was found to be sensitive to increased axial nozzle-wheel clearance. A cast nozzle giving a turbine brake efficiency of 0.525 at an axial running clearance of 0.035 inch gave a brake efficiency of 0.475 when the clearance was increased to 0.095 inch for the same inlet-gas conditions and blade-jet speed ratio. If the basis for computing the isentropic power available to the turbine is the temperature inside the nozzle rather then the temperature in the inlet-gas pipe, an increase in turbine efficiency of about 0.01 is indicated.
Contributing Partner: UNT Libraries Government Documents Department