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Linear Amplifiers

Description: Problems in the design of linear amplifiers are presented from the point of view of the radio engineer.
Date: September 7, 1949
Creator: Schultz, M. A.
Partner: UNT Libraries Government Documents Department

Reactor Engineering Division Quarterly Report, June 1, 1949 - August 31, 1949

Description: Report issued by the Argonne National Laboratory covering the quarterly report from the Reactor Engineering Division. A summary of reactor programs, designs, development, and experiments are presented. This report includes tables, illustrations, and photographs.
Date: October 7, 1949
Creator: Argonne National Laboratory. Reactor Engineering Division.
Partner: UNT Libraries Government Documents Department

Method of Determining Centrifugal-Flow-Compressor Performance With Water Injection

Description: Memorandum presenting a method for computing the isentropic and actual enthalpy change between the inlet and outlet of a centrifugal-flow compressor when water injection is used. The method of calculation is based on fluid property values given in steam and air tables.
Date: September 7, 1949
Creator: Hamrick, Joseph T. & Beede, William L.
Partner: UNT Libraries Government Documents Department

Flight Investigation at High Speeds of the Drag of Three Airfoils and a Circular Cylinder Representing Full-Scale Propeller Shanks

Description: "Tests have been made at high speeds to determine the drag of models, simulating propeller shanks, in the form of a circular cylinder and three airfoils, the NACA 16-025, the NACA 16-040, and the NACA 16-040 with the rear 25 percent chord cut off. All the models had a maximum thickness of 4 1/2 inches to conform with average propeller-shank dimensions and a span of 20 1/4 inches. For the tests the models were supported perpendicular to the lower surface of the wing of an XP-51 airplane (p. 277).
Date: June 7, 1946
Creator: Barlow, William H.
Partner: UNT Libraries Government Documents Department

The Effect of Air Jets Simulating Chines or Multiple Steps on the Hydrodynamic Characteristics of a Streamline Fuselage

Description: Memorandum presenting preliminary tests in order to determine the effect of forced ventilation on the hydrodynamic characteristics of a scale model of a streamline fuselage of a hypothetical transonic airplane. The forced ventilation consisted of air ejected at about 300 feet per second through small orifices distributed over the fuselage bottom in a series of patterns simulating chines or multiple steps. Results regarding resistance, effective hydrodynamic lift, trim, spray, and air flow are provided.
Date: January 7, 1949
Creator: Weinflash, Bernard
Partner: UNT Libraries Government Documents Department

Flight tests of thermal ice-prevention equipment in the XB-24F airplane

Description: Report presenting performance tests of thermal ice-prevention equipment designed and installed in the XB-24F airplane in icing and non-icing conditions. The recorded temperature and air-flow data, and the calculated quantities of heat flow throughout the system are presented in tabular form.
Date: October 7, 1943
Creator: Neel, Carr B. & Jones, Alun R.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Description: Report presenting an investigation of combustion occurring downstream of various turbulence promoters in a 20-inch length of a 1 7/8-inch inside-diameter, water-jacketed tubing using premixed vaporized fuel and air. Among the turbulence promoters investigated were flat plates perforated with 1/8-inch diameter holes, 1/4-inch diameter holes, and a single large hole to give 12.4, 17.2, and 21.5 percent open area respectively.
Date: June 7, 1948
Creator: Haddock, Gordon W. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

Static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation

Description: Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range with the all-movable horizontal tail installed and removed.
Date: November 7, 1949
Creator: Lange, Roy H. & McLemore, Huel C.
Partner: UNT Libraries Government Documents Department

Pressure-distribution measurements over an extensible leading-edge flap on two wings having leading-edge sweep of 42 degrees and 52 degrees

Description: Report presenting an investigation of the pressure distribution over a leading-edge flap in the 19-foot pressure tunnel. Testing occurred on 42 degree and 52 degree sweptback wings of NACA 64(sub 1)-112 sections, with the 42 degree wing being used in conjunction with a circular cross-section fuselage in a high-wing combination.
Date: March 7, 1949
Creator: Salmi, Reino J.
Partner: UNT Libraries Government Documents Department

A comparison of the simulated-altitude performance of two turbojet combustor types

Description: Report presenting a comparison of the performance of a German Jumo 004 can-type combustor and the performance of two contemporary United States turbojet combustors to determine whether the Jumo 004 was more advanced and to determine whether there are basic, inherent differences in the performance achieved with the can or annular combustor type. Results regarding altitude operational limits, combustion efficiency, pressure loss, and temperature profile at combustor outlet are provided.
Date: October 7, 1948
Creator: Bolz, Ray E.; Schroeter, Thomas T. & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Description: Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.
Date: May 7, 1948
Creator: Perkins, Edward W.
Partner: UNT Libraries Government Documents Department

Investigation of ceramic, graphite, and chrome-plated graphite nozzles on rocket engine

Description: The use of ceramic material for rocket nozzles and the effectiveness of preventing oxidation and erosion of graphite nozzles by chrome-plating the internal surface were investigated. A supported ceramic nozzle, cracked by initial operation, was operated a second time without further cracking or damage. Chrome-plating the internal surface of graphite nozzles effectively prevented oxidation and erosion that occurred during operation with unprotected graphite.
Date: March 7, 1949
Creator: Kinney, George R. & Lidman, William G.
Partner: UNT Libraries Government Documents Department

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Description: Report presenting an investigation to determine the effects of a vertical tail with the leading edge swept back 63 degrees on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. The aerodynamic characteristics in sideslip with and without the vertical tail are also presented. Results regarding the directional stability, rudder effectiveness, and rudder hinge moments are described.
Date: October 7, 1949
Creator: McCormack, Gerald M.
Partner: UNT Libraries Government Documents Department

Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Description: Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditching station. The airplane will settle in the water rapidly to the level of the wings with only gradual changes in attitude. The maximum longitudinal deceleration will be between 1.2g and 1.7g in a calm-water ditching.
Date: October 7, 1948
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department

Test-stand investigation of a rectangular ram-jet engine

Description: Report presenting a test-stand investigation conducted on a rectangular ramjet engine design for installation in an aircraft wing. The engine operated without excessive engine noise or vibration over the entire range of operating conditions. Results regarding inlet velocity, exhaust flame characteristics, fuel-air ratio, and total-temperature rise are provided.
Date: May 7, 1947
Creator: Black, Dugald O. & Messing, Wesley E.
Partner: UNT Libraries Government Documents Department

Development of NACA submerged inlets and a comparison with wing leading-edge inlets for a 1/4-scale model of a fighter airplane

Description: Characteristics of NACA submerged duct entries and wing leading-edge inlets designed for a 1/4 scale flow model of a fighter-type airplane powered by a jet engine in the fuselage are presented.
Date: August 7, 1947
Creator: Mossman, Emmet A. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 256th week of the war, 138th week of U.S. participation

Description: Front: Text describes action on various war fronts : Eastern front, France, Italy, Southwest Pacific, Marianas, Far East. Maps: North Sea, English Channel, and Bay of Biscay with surrounding countries as viewed from England. Japanese targets hit by B-20s 15 June, 7 July, and 29 July. Current battle line between Poland and the U.S.S.R. Distance map between Stalingrad and Warsaw. Photographs: U.S. soldiers move warily toward hedgerows in the fields of Normandy; View of Florence, Italy from the Piazzole Michaelango showing the Arno River, Palazzo Vecchio and the cathedral; Underbelly view of the B-29 Superfortress. Back: Text and illustrations highlight the responsibilities of the Navy's Amphibious Forces. Includes insignia and list of battles.
Date: August 7, 1944
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, February 7, 1944 : week of January 27 to February 3, 230th week of the war, 112th week of U.S. participation

Description: Front: Text describes action on various war fronts: Central Pacific, Italy, USSR, Air war, Burma. Maps show Marshall Islands; Allied advances during the week. Photographs: Artillery technique in Italy; American helmets of the 25th Division and hats of a New Zealand brigade mingle at Vella Lavella; Navy mobile photographic laboratory comes ashore in the Solomons; African Goummiers of the Fifth Army don traditional gowns over American uniforms; Pilots of the 99th Fighter Squadron talk tactics; German transport vehicles retreat from the Soviet front; Photographer positioned where a .50 caliber gun would be mounted in a Navy reconnaissance Liberator; Soldiers stuff 250 pamphlets into each 25 pound shell in Italy; Fifth Army infantry battalion's 81 mm. mortars travel by mule in Venafro. Back: Jap army uniforms. Color illustrations of seasonal and miscellaneous uniforms of officers and men.
Date: February 7, 1944
Creator: [United States.] Army Service Forces. Morale Services Division. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees

Description: Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.
Date: June 7, 1949
Creator: Schneiter, Leslie E. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department