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One-Dimensional Flows of an Imperfect Diatomic Gas

Description: "With the assumptions that Berthelot's equation of state accounts for molecular size and intermolecular force effects, and that changes in the vibrational heat capacities are given by a Planck term, expressions are developed for analyzing one-dimensional flows of a diatomic gas. The special cases of flow through normal and oblique shocks in free air at sea level are investigated. It is found that up to a Mach number 10 pressure ratio across a normal shock differs by less than 6 percent from its ideal gas value; whereas at Mach numbers above 4 the temperature rise is considerable below and hence the density rise is well above that predicted assuming ideal gas behavior" (p. 239).
Date: December 30, 1948
Creator: Eggers, A. J., Jr.
Partner: UNT Libraries Government Documents Department

A General Small-Deflection Theory for Flat Sandwich Plates

Description: "A small-deflection theory is developed for the elastic behavior of orthotropic flat plates in which deflections due to shear are taken into account. In this theory, which covers all types of flat sandwich construction, a plate is characterized by seven physical constants (five stiffnesses and two Poisson ratios) of which six are independent. Both the energy expression and the differential equations are developed. Boundary conditions corresponding to simply supported, clamped, and elastically restrained edges are considered" (p. 1).
Date: September 30, 1947
Creator: Libove, Charles & Batdorf, S. B.
Partner: UNT Libraries Government Documents Department

Investigation of Performance of Single-Stage Axial-Flow Compressor Using NACA 5509-34 Blade Section

Description: Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.
Date: September 30, 1948
Creator: Mankuta, Harry & Guentert, Donald C.
Partner: UNT Libraries Government Documents Department

Preliminary Tests of a Buffet Stall-Warning Device on a 1/5-Scale Model of the Republic XP-84 Airplane

Description: "During the first flight tests of the Republic XP-84 airplane it was discovered that there was a complete lack of stall warning. A short series of development tests of a suitable stall-warning device for the airplane was therefore made on a 1/5-scale model in the Langley 300 MPH 7- by 10-foot tunnel. Two similar stall-warning devices, each designed to produce early root stall which would provide a buffet warning, were tested" (p. 1).
Date: October 30, 1946
Creator: Tucker, Warren A. & Comisarow, Paul
Partner: UNT Libraries Government Documents Department

Equations of State of Elements Based on the Generalized Fermi-Thomas Theory

Description: The Fermi-Thomas model has been used to derive the equation of state of matter at high pressures and at various temperatures. Calculations have been carried out both without and with the exchange terms. Discussion of similarity transformations lead to the virial theorem and to correlation of solutions for different Z-values.
Date: April 30, 1949
Creator: Feynman, R.P.; Metropolis, N. & Teller, E.
Partner: UNT Libraries Government Documents Department

Effects of Compressibility on the Flow Past Thick Airfoil Sections

Description: "Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photographs indicated that at Mach numbers approximately 0.05 above the critical Mach number a speed region was reached in which the flow oscillated rapidly and the separation point and the location of the shock wave were unstable" (p. 1).
Date: January 30, 1947
Creator: Daley, Bernard N. & Humphreys, Milton D.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, November 30, 1942 : week of November 20 to November 27

Description: Text describes action on various war fronts: Russia, Tunisia, Libya, West Africa, Martinique, New Guinea, Solomons. Front: large world map is keyed to text and illustrates time zones around the world. Inset maps: Offensive in New Guinea; Tunisia; North Africa; South Russia. Photographs: Guadalcanal; Jeeps in Russia; Unloading in North Africa; U.S. patrol landed on one of the isolated islands of the Aleutian group. Back: Aircraft insignia. Aircraft insignia are subject to change constantly. These are based on information available up to November 30, 1942.
Date: November 30, 1942
Creator: [United States.] Army Orientation Course
Partner: UNT Libraries Government Documents Department

Domestic disturbances

Description: "This manual presents the principles for the employment of troops during domestic disturbances and the essential substances of the more important laws relating to the employment of military forces in the aid of civil authorities with the applicable War Department policies"
Date: July 30, 1945
Creator: United States. War Department.
Partner: UNT Libraries Government Documents Department

Simulated Altitude Performance of Combustor of Westinghouse 19XB-1 Jet-Propulsion Engine

Description: From Summary: "A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turbojet engine at various altitudes and engine speeds. The combustion efficiencies and the altitude operational limits were determined; data were also obtained on the character of the combustion, the pressure drop through the combustor, and the combustor-outlet temperature and velocity profiles. At altitudes about 10,000 feet below the operational limits, the flames were yellow and steady and the temperature rise through the combustor increased with fuel-air ratio throughout the range of fuel-air ratios investigated. At altitudes near the operational limits, the flames were blue and flickering and the combustor was sluggish in its response to changes in fuel flow."
Date: November 30, 1948
Creator: Childs, J. Howard & McCafferty, Richard J.
Partner: UNT Libraries Government Documents Department

Effect of tunnel configuration and testing technique on cascade performance

Description: "An investigation has been conducted to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynolds number, and tunnel end-wall condition upon the performance of airfoils in cascades. A representative compressor-blade section (the NACA 65-(12)(10) of aspect ratios of 1, 2, and 4 has been tested at low speeds in cascades with solid and with porous side walls. Two-dimensional flow was established in porous-wall cascades of each of the three aspect ratios tested; the flow was not two-dimensional in any of the solid-wall cascades" (p. 263).
Date: November 30, 1949
Creator: Erwin, John R. & Emery, James C.
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Description: From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbers up to 0.94."
Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D.
Partner: UNT Libraries Government Documents Department

Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine

Description: Report presenting an investigation to obtain fundamental information required for the design of a satisfactory tail-pipe burner for augmenting turbojet engine thrust. Investigations were also conducted to determine the combustion and pressure-drop characteristics of the most satisfactory burner, to develop a method of controlling the burner-outlet temperature distribution, and to improve the burner ignition characteristics.
Date: October 30, 1947
Creator: Gabriel, David S.; Martinson, E. Vincent & Essig, Robert H.
Partner: UNT Libraries Government Documents Department

Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department

Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Description: Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.
Date: July 30, 1948
Creator: Wilcox, Fred A.; Perchonok, Eugene & Wishnek, George
Partner: UNT Libraries Government Documents Department

Performance of Axial-Flow Supersonic Compressor on XJ-55-FF-1 Turbojet Engine 1: Preliminary Performance of Compressor

Description: An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ-55-FF-1 turbo Jet engine. The test unit consisted of a row of inlet guide vanes and a supersonic rotor; the stator vanes after the rotor were omitted. The maximum pressure ratio produced in the single stage was 2.28 at an equivalent tip speed or 1814 feet per second with an adiabatic efficiency of approximately 0.61, equivalent weight flow of 13.4 pounds per second. The maximum efficiency of 0.79 was obtained at an equivalent tip speed of 801 feet per second.
Date: January 30, 1949
Creator: Hartmann, Melvin J. & Graham, Robert C.
Partner: UNT Libraries Government Documents Department

Stability derivatives at supersonic speeds of thin rectangular wings with diagonals ahead of tip Mach lines

Description: The investigation includes steady and accelerated vertical and longitudinal motions and steady rolling, yawing, sideslipping, and pitching for Mach numbers and aspect ratios greater than those for which the Mach line from the leading edge of the tip section intersects the trailing edge of the opposite tip section. The stability derivatives are derived with respect to principal body axes and then transformed to a system of stability axes. Theoretical results are obtained, by means of the linearized theory, for the surface-velocity-potential functions, surface-pressure distributions, and stability derivatives for various motions at supersonic speeds of thin flat rectangular wings without dihedral.
Date: June 30, 1948
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Description: Report presenting the combustion efficiencies of 10 experimental jet-propulsion fuels that are approximately 200 degrees Fahrenheit cuts of five selected crudes available in large quantities in a turbojet engine combustor at altitude conditions.
Date: April 30, 1947
Creator: Cleaves, Alden P. & Carver, Mildred S.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 294th week of the war, 176th week of U.S. participation

Description: Front: Maps: Soviets Enter Berlin ; Pacific Allies Gain. Inset map: Berlin. Back: [text and ill.]: San Francisco Conference -- Geared to peace and progress -- International organization proposed at Dumbarton Oaks.
Date: April 30, 1945
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 268th week of the war, 150th week of U.S. participation

Description: Front: Text describes action on various war fronts: Philippine action, Chinese offensive, Western front drives, Soviet victory guns, Italian progress. Maps: Manila (Philippines); Pacific area; Philippine Islands; European front; Netherlands. Back: Your submarine, versatile warship. Cutaway cross section shows key features of a submarine. 3 photographs illustrate life aboard a submarine. Includes text from an Official Report of Admiral Ernest J. King, USN, Commander in Chief U.S. Fleet, and chief of Naval Operations, to the Secretary of the Navy.
Date: October 30, 1944
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department