104 Matching Results

Search Results

Lathes

Description: A guide to the operation and maintenance of lathes for general shop work.
Date: November 29, 1940
Creator: United States. Army. Air Corps.
Partner: UNT Libraries Government Documents Department

Application of the Method of Characteristics to Supersonic Rotational Flow

Description: "A system for calculating the physical properties of supersonic rotational flow with axial symmetry and supersonic rotational flow in a two-dimensional field was determined by use of the characteristics method. The system was applied to the study of external and internal flow for supersonic inlets with axial symmetry. For a circular conical inlet the shock that occurred at the lip of the inlet became stronger as it approached the axis of the inlet and became a normal shock at the axis" (p. 111).
Date: April 29, 1946
Creator: Ferri, Antonio
Partner: UNT Libraries Government Documents Department

Line-Vortex Theory for Calculation of Supersonic Downwash

Description: "The perturbation field induced by a line vortex in a supersonic stream and the downwash behind a supersonic lifting surface are examined to establish approximate methods for determining the downwash behind supersonic wings. Lifting-lines methods are presented for calculating supersonic downwash. A bent lifting-line method is proposed for computing the downwash field behind swept wings. When applied to triangular wings with subsonic leading edges, this method gives results that, in general, are in good agreement with the exact linearized solution" (p. 635).
Date: April 29, 1949
Creator: Mirels, Harold & Haefeli, Rudolph C.
Partner: UNT Libraries Government Documents Department

The Effects of Fuel Sloshing on the Lateral Stability of a Free-Flying Airplane Model

Description: Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the lateral motions of the model appeared jerky.
Date: June 29, 1948
Creator: Smith, Charles C., Jr.
Partner: UNT Libraries Government Documents Department

Flight Investigation of Thrust Augmentation of a Turbojet Engine by Water-Alcohol Injection

Description: Memorandum presenting an investigation of thrust augmentation by the injection of water-alcohol mixtures into the compressor inlets of a turbojet engine with a centrifugal-flow-type compressor at altitudes of sea level, 5000 feet, and 10,000 feet. The investigation was made to determine the water-alcohol mixture and the injection rate for optimum thrust augmentation. At a standard NACA altitude of 10,000 feet and an engine speed of 16,000 rpm, the mixture and injection rate for optimum thrust augmentation was found to be 20-percent alcohol to water by weight injected at a rate of approximately 1.45 pounds per second.
Date: September 29, 1947
Creator: Ellisman, Carl
Partner: UNT Libraries Government Documents Department

Fuel Tests on an I-16 Jet-Propulsion Engine at Static Sea-Level Conditions

Description: Memorandum presenting an investigation of the effect of fuel composition and boiling point on the performance of the type of I-16 jet-propulsion engine. Testing occurred with 14 fuels embodying different types of hydrocarbon and with a range of boiling points. The results indicated that fuel composition and boiling range have a negligible effect on engine thrust, rotor speed, and gas temperatures for the principal types of hydrocarbon fuel when used for short periods of time.
Date: April 29, 1947
Creator: Bolz, Ray E. & Meigs, John B.
Partner: UNT Libraries Government Documents Department

A Study of Skin Temperatures of Conical Bodies in Supersonic Flight

Description: Memorandum presenting a comparison between the time history of skin temperature measured on the nose of a V-2 and the temperature computed using Eber's experimental relation for heat-transfer coefficients for conical bodies under supersonic conditions. A general method developed for making skin-temperature calculations is used to compute the variation of skin temperature with time for a wide range of values of the pertinent parameters. Results regarding the validity of skin-temperature calculations, ranges of skin temperature, and skin temperatures for a typical supersonic airplane are provided.
Date: January 29, 1948
Creator: Huston, Wilber B.; Warfield, Calvin N. & Stone, Anna Z.
Partner: UNT Libraries Government Documents Department

Theory of High Frequency Rectification by Silicon Crystals

Description: The excellent performance of British ''red dot'' crystals is explained as due to the knife edge contact against a polished surface. High frequency rectification depends critically on the capacity of the rectifying boundary layer of the crystal. C. For high conversion efficiency, the product of this capacity and of the ''forward'' (bulk) resistance R{sub b} of the crystal must be small. For a knife edge, this product depends primarily on the breadth of the knife edge and very little upon its length. The contact can therefore have a rather large area which prevents burn-out. For a wavelength of 10 cm. the computations show that the breadth of the knife edge should be less than about 10{sup -3} cm. For a point contact the radius must be less than 1.5 x 10{sup -3} cm. and the resulting small area is conductive to burn-out. The effect of ''tapping'' is probably to reduce the area of contact.
Date: October 29, 1942
Creator: Bethe, H.A.
Partner: UNT Libraries Government Documents Department

A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft

Description: An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally loaded expansion turbine in conjunction with a supersonic diffuser would maintain tolerable ventilating air temperature, at least up to a flight Mach number of 2. The most complex system considered,composed of compressor, intercooler, and expansion turbine with the intercooler cooling air decreased in temperature by expansion through an auxiliary turbine is capable of maintaining a ventilation air temperature less than ambient temperature up to a flight Mach number of 3.7.
Date: April 29, 1947
Creator: Stalder, Jackson R. & Wadleigh, Kenneth R.
Partner: UNT Libraries Government Documents Department

Flight Measurements of Lateral and Directional Stability and Control Characteristics of the Grumman F8F-1 Airplane

Description: "This paper presents the results of flight tests to determine the lateral and directional stability and control characteristics of the Grumman F8F-1 airplane with three vertical-tail configurations. The data presented herein have no bearing on the performance characteristics of the airplane, which were not measured but which were considered to be exceptionally good. The conclusions reached regarding the lateral and directional stability and control characteristics are summarized in this report" (p. 1).
Date: January 29, 1948
Creator: Crane, H. L. & Reeder, J. P.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, March 29, 1943 : week of March 19 to March 26, 185th week of the war, 67th week of U.S. participation

Description: Front: Text describes action on various war fronts: Tunisia, Air offensive, Submarines, Southwest Pacific, Russia, China. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Gulf of Gabes region, Moscow region. Includes photographs: Counter attack at Kasserine, New Navy planes, Enemy hospital ship. Back: Gas. 5 gases are illustrated and described; Lewisite, mustard, tear gas, phosgene and clorpicrin.
Date: March 29, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 246th week of the war, 128th week of U.S. participation

Description: Front: Text describes action on various war fronts: Italy, Pacific, USSR, China, Southeast Asia, Western Europe. Maps: Central Italy showing current offensive areas and the battle line as of 11 May, 1944; Extent of Allied ground force operations. Includes photographs: 20,000 ft. column of smoke rising from Ploesti, Romania; Supply column heads north through Castelforte, Italy; American soldier walks through piles of rubble in the aftermath of heavy shelling; Amphibious "ducks" outside Anzio, laden with supplies for Fifth Army troops; Tanks emerge from the Assam Hills in northern India; Army nurse Lt. Jane Easton of Atlantic City, NJ and nurse Doru Chu of China tend to Corp. George Sammy of Gary, Ind. in China, Lt. La Retta Matthews of Lakeland, FL and Lt. Carolyn Taylor, Douglaston, L.I., N.Y. converse with a fabric shop owner in a Chinese city. Back: New Guinea. Map (continuation of map issued in Newsmap v. 2, no. 37).
Date: May 29, 1944
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Longitudinal characteristics and aileron effectiveness of a midwing airplane from high-speed wind tunnel tests

Description: Report presenting wind-tunnel tests of a 0.175-scale model of a midwing airplane in order to determine the high-speed longitudinal characteristics, to test devices for improving longitudinal control at high Mach numbers, and to determine the aileron effectiveness at high Mach numbers. Force and moment coefficients are computed from test data. Control forces, elevator angle, and aileron angle for several flight conditions are predicted.
Date: September 29, 1944
Creator: Hall, Charles F. & Mannes, Robert L.
Partner: UNT Libraries Government Documents Department

Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Description: "A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting" (p. 425).
Date: December 29, 1944
Creator: Sinnette, John T., Jr. & Voss, William J.
Partner: UNT Libraries Government Documents Department

Investigation of Stability and Control Characteristics of a 1/10-Scale Model of a Canadian Tailless Glider in the Langley Free-Flight Tunnel

Description: "An investigation of the stability and control characteristics of a 1/10-scale model of a Canadian tailless glider has been conducted in the 10 Langley free-flight tunnel. The glider designated the N.R.L. tailless glider has a straight center section and outboard panels sweptback 43 deg. along the leading edge of the wing. The aspect ratio is 5.83 and the taper ratio is 0.323. From the results of the investigation and on the basis of comparison with higher-scale static tests of the National Research Council of Canada, it is expected that the longitudinal stability of the airplane will be satisfactory with flap up but unsatisfactory near the stall with flap down" (p. 1).
Date: March 29, 1949
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

On the Flow of a Compressible Fluid by the Hodograph Method. II - Fundamental Set of Particular Flow Solutions of the Chaplygin Differential Equation

Description: From Summary: "The differential equation of Chaplygin's jet problem is utilized to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The particular solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows. It is shown that the geometric-mean type of velocity correction formula introduced in part I has significance as an over-all type of approximation in the subsonic range."
Date: September 29, 1944
Creator: Garrick, I. E. & Kaplan, Carl
Partner: UNT Libraries Government Documents Department

Investigation of carbon deposition in an I-16 jet-propulsion engine at static sea-level conditions

Description: Report presenting a study of the effect of fuel properties on carbon deposition in jet-propulsion engine combustors using seven fuels: kerosene, Diesel fuel oil, toluene, xylene, 62-octane gasoline, a commercial solvent, and AN-F-32 (JP-1) in an I-16 engine at static sea-level conditions and constant rotor speed. Results regarding the reproducibility of data, reduced exhaust-jet-nozzle area, and fuel comparison are provided.
Date: April 29, 1947
Creator: Jonash, Edmund R.; Barnett, Henry C. & Stricker, Edward G.
Partner: UNT Libraries Government Documents Department