UNT Libraries Government Documents Department - 13 Matching Results

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Methyl Methacrylate Casting Resin

Description: Abstract: "This report describes work done to improve the casting characteristics of methyl methacrylete resin under CMR-6-18 authorization. The experimental program was initiated with the objectives of decreasing casting time, bubble formation and shrinkage. It has been found that by use of a common solvent for monomer and polymer concentration in monomer can be attained greater than any previously reported in preparation of a methacrylate casting resign. Incorporation of this greater amount o… more
Date: January 8, 1948
Creator: Church, J. S. & Tyler, H. R.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1

Description: Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.
Date: July 8, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
open access

Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system

Description: Investigation of a single-offset-duct system designed to prevent entrance of water into a turbojet engine was conducted on a half-scale nacelle model. An investigation was made to determine ram-pressure recovery and radial velocity profiles at the compressor section and icing characteristics of such a duct system. At a design inlet velocity of 0.77, the maximum ram-pressure recovery attained with effective water-separating inlet was 77 percent, which is considerably less than attainable with a … more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
open access

Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets

Description: Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at in… more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
open access

Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous … more
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Item Type: Refine your search to only Report
open access

Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2

Description: "The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed … more
Date: July 8, 1948
Creator: Mottard, Elmo J. & Ruggles, Robert D.
Item Type: Refine your search to only Report
open access

Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet

Description: Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date: June 8, 1948
Creator: Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
Item Type: Refine your search to only Report
open access

Notes on Geared Tabs at Supersonic Speeds

Description: Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
Item Type: Refine your search to only Report
open access

Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Description: Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.
Date: July 8, 1948
Creator: Baron, Burnett; Dowman, Harry W. & Dackis, William C.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Control Characteristics of a Semispan Model of a Supersonic Airplane Configuration at Transonic Speeds From Tests by the NACA Wing-Flow Method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane model with a long slender fuselage, straight wing, and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections. Measurements of the normal force and pitching moments at various angles of attack with five different stabilizer angles of incidence were recorded. The tests were carried out a range of … more
Date: November 8, 1948
Creator: Silsby, Norman S. & McKay, James M.
Item Type: Refine your search to only Report
open access

Some preliminary results in the determination of aerodynamic derivatives of control surfaces in the transonic speed range by means of a flush-type electrical pressure cell

Description: Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.
Date: October 8, 1948
Creator: Erickson, Albert L. & Robinson, Robert C.
Item Type: Refine your search to only Report
open access

Yaw Characteristics of a 52 Degree Sweptback Wing of NACA 64(Sub 1)-112 Section With a Fuselage and With Leading-Edge and Split Flaps at Reynolds Numbers From 1.93 X 10(Exp 6) to 6.00 X 10(Exp 6)

Description: Report presenting low-speed testing in the pressure tunnel to determine the aerodynamic characteristics in yaw of a 52 degree sweptback wing with aspect ratio 2.88 and taper ratio 0.625 with NACA 64(sub 1)-112 airfoil sections. Testing included an investigation of the effects on the lateral stability of a fuselage and leading-edge and split flaps. Results regarding the lateral stability parameters of a plain wing, effect of flaps on the lateral stability parameters, effect of scale, and airflow… more
Date: November 8, 1948
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
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