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Radio communication.

Description: Discusses "radio communication fundamentals and the methods and technique involved in the installation and operation of radio communication equipment."
Date: January 28, 1944
Creator: United States. War Department.
Partner: UNT Libraries Government Documents Department

Performance of J-33-A-21 and J-33-A-23 Compressors With and Without Water Injection

Description: "In an investigation of the J-33-A-21 and the J-33-A-23 compressors with and without water injection, it was discovered that the compressors reacted differently to water injection although they were physically similar. An analysis of the effect of water injection on compressor performance and the consequent effect on matching of the compressor and turbine components in the turbojet engine was made. The analysis of component matching is based on a turbine flow function defined as the product of the equivalent weight flow and the reciprocal of the compressor pressure ratio" (p. 1).
Date: January 28, 1948
Creator: Beede, William L.
Partner: UNT Libraries Government Documents Department

Investigations on the Incompletely Developed Plane Diagonal-Tension Field

Description: This report presents the results of an investigation on the incompletely developed diagonal-tension field. Actual diagonal-tension beams work in an intermediate stage between pure shear and pure diagonal tension; the theory developed by Wagner for diagonal tension is not directly applicable.
Date: March 28, 1940
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

Investigations of Effects of Surface Temperature and Single Roughness Elements on Boundary-Layer Transition

Description: "The laminar boundary layer and the position of the transition point were investigated on a heated flat plate. It was found that the Reynolds number of transition decreased as the temperature of the plate is increased. It is shown from simple qualitative analytical considerations that the effect of variable viscosity in the boundary layer due to the temperature difference produces a velocity profile with an inflection point if the wall temperature is higher than the free-stream temperature" (p. 587).
Date: August 28, 1946
Creator: Liepmann, Hans W. & Fila, Gertrude H.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, September 28, 1942 : week of September 18 to September 25

Description: Front: Text describes action on various war fronts: North Africa, Russia, Madagascar, Solomons, New Guinea, China, Burma, Western Europe. Large world map is keyed to text and illustrates time zones around the world. Inset maps show the drive on Port Moresby, East China, South Russia. Includes photographs: "Jap midget starts new mission", Testing M4 tanks, Japanese target [Port Moresby air field], Russian front-- Kuban sector, Victory fleet. Back: Jungle Warfare. 18 photographs showing scenes of jungle warfare accompanied by text describing the challenges faced by soldiers in that environment.
Date: September 28, 1942
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Ice protection of turbojet engines by inertia separation of water 1: alternate-duct system

Description: Aerodynamic and icing investigations of internal water-inertia separation inlets designed to prevent automatically entrance of large quantities of water into a turbojet engine in icing conditions was conducted on a one-half scale model. A simplified analytical approach to the design of internal water-inertia separation inlets is included. Results show that in order to be effective in preventing screen and guide-vane icing for an inlet of this type, a ram-pressure recovery of 75 percent was attained at design inlet-velocity ratio in an icing condition. For nonicing operation, ram-pressure recovery is comparable to direct-ram inlet.
Date: May 28, 1948
Creator: von Glahn, Uwe
Partner: UNT Libraries Government Documents Department

A theoretical analysis of the effect of time lag in an automatic stabilization system on the lateral oscillatory stability of an airplane

Description: "A method is presented for determining the effect of time lag in an automatic stabilization system on the lateral oscillatory stability of an airplane. The method is based on an analytical-graphical procedure. The critical time lag of the airplane-autopilot system is readily determined from the frequency-response analysis. The method is applied to a typical present-day airplane equipped with an automatic pilot sensitive to yawing acceleration and geared to the rudder so that rudder control is applied in proportion to the yawing acceleration" (p. 1).
Date: October 28, 1949
Creator: Sternfield, Leonard & Gates, Ordway B., Jr.
Partner: UNT Libraries Government Documents Department

Ground Tests of a Radial Air-Cooled Engine to Correct a Poor Circumferential Pressure-Recovery Distribution

Description: "This report presents the results of the tests of a power-plant installation to improve the circumferential pressure-recovery distribution at the face of the engine. An underslung "C" cowling was tested with two propellers with full cuffs and with a modification to one set of cuffs. Little improvement was obtained because the base sections of the cuffs were stalled. A set of guide vanes boosted the over-all pressures and helped the pressure recoveries for a few of the cylinders" (p. 1).
Date: January 28, 1948
Creator: Gallagher, James J.
Partner: UNT Libraries Government Documents Department

Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model

Description: Report presenting wind-tunnel tests up to a Mach number of 0.85 to determine the effects of wing-tip gun turrets on the aerodynamic characteristics of a typical bomber-wing model. Lift, drag, and pitching-moment data are presented for the wing alone; for the wing with the turrets in the clean condition; and for the wing and the turrets with guns and sighting equipment. The turrets had negligible effect on the lift and pitching-moment characteristics of the wing.
Date: March 28, 1949
Creator: Boddy, Lee E. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

High-speed wind-tunnel tests of a 1/78-scale model of the Lockheed YP-80A airplane

Description: Report presenting an investigation to determine the high-speed performance and static longitudinal stability and control characteristics of a model of the Lockheed YP-80A airplane. High-speed aerodynamic characteristics are presented for speeds up to Mach number 0.96. Results regarding the scale effects, longitudinal stability, and longitudinal-control effectiveness are provided.
Date: May 28, 1948
Creator: Olson, Robert N. & Lawrence, Leslie F.
Partner: UNT Libraries Government Documents Department

Investigation of wing characteristics at a Mach number of 1.53 2: swept wings of taper ratio 0.5

Description: Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Date: June 28, 1948
Creator: Vincenti, Walter G.; Van Dyke, Milton D. & Matteson, Frederick H.
Partner: UNT Libraries Government Documents Department

Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Description: Report presenting a theoretical analysis of thrust augment of turbojet engines by tail-pipe burning and charts from which the thrust augmentation produced may be evaluated from the normal engine data and performance of the tail-pipe burner. Results regarding general curves and illustrative curves are provided.
Date: January 28, 1947
Creator: Bohanon, H. R. & Wilcox, E. C.
Partner: UNT Libraries Government Documents Department

Investigation of the diborane - hydrogen peroxide propellant combination

Description: Report presenting the results of two runs made with liquid diborane and hydrogen peroxide in a small-scale rocket engine. The first run was very erratic and modifications were made to the testing apparatus and procedures for the second run. In the second run, the combustion started immediately and continued smoothly for 12 seconds of operation.
Date: May 28, 1948
Creator: Rowe, William H.; Ordin, Paul M. & Diehl, John M.
Partner: UNT Libraries Government Documents Department

An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85

Description: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date: April 28, 1947
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of 16-inch diameter supersonic ram-jet unit

Description: Report presenting an investigation of a series of 16-inch-diameter ramjet engine in free flight in order to determine the performance of ramjet units in flight at supersonic speeds and to study methods for improving the performance. Results regarding the telemeter data recorded by ground stations, static pressures, variation of altitude with time after release, variation of flight velocities, and fuel-air ratio are provided. Partial failure of the measuring equipment prevented a complete evaluation of engine performance.
Date: May 28, 1948
Creator: Kinghorn, George F. & Disher, John H.
Partner: UNT Libraries Government Documents Department