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Serial/Series Title
NACA Research Memorandums
155
Atomic Energy Commission Reports
64
NACA Technical Reports
35
Hanford Works Reports
26
HW (Series)
20
Oak Ridge National Laboratory Reports
19
University of California Radiation Laboratory Reports
16
BNL (Series)
12
Brookhaven National Laboratory Reports
12
GJBX
9
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354 Matching Results
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Investigation of Turbine of Mark 25 Torpedo Power Plant with Five Nozzle Designs
"Efficiency investigations were made on the two-stage turbine from a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. A method was developed for measuring the change in turbine clearances with changed operating conditions. The turbine was found to be most efficient with a cast nozzle having a sharp-edged inlet to the nine nozzle ports" (p. 1).
Date:
October 8, 1947
Creator:
Hoyt, Jack W. & Kottas, Harry
Object Type:
Report
System:
The UNT Digital Library
Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing
Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date:
December 8, 1947
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 12, 1947 to July 18, 1947 at Clinton County Army Air Field, Ohio
The gust and draft velocities from records of NACA instruments installed in P-61c airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from July 12, to July 18, 1947 are presented.
Date:
December 8, 1947
Creator:
Funk, Jack
Object Type:
Report
System:
The UNT Digital Library
An experimental investigation of the design variables for NACA submerged duct entrances
Information concerning the parameters and design variables affecting an NACA submerged duct design is presented.
Date:
January 8, 1948
Creator:
Mossman, Emmet A. & Randall, Lauros M.
Object Type:
Report
System:
The UNT Digital Library
Methyl Methacrylate Casting Resin
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 of polymer has produced the desired effects. A bibliography of relevant literature is included to which reference is made in the text."
Date:
January 8, 1948
Creator:
Church, J. S. & Tyler, H. R.
Object Type:
Report
System:
The UNT Digital Library
Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system
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 direct-ram inlet. Continuous heating of the accessory-housing surface would be required for inlets that have a small ice storage space.
Date:
June 8, 1948
Creator:
von Glahn, Uwe
Object Type:
Report
System:
The UNT Digital Library
Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets
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 inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack.
Date:
June 8, 1948
Creator:
von Glahn, Uwe
Object Type:
Report
System:
The UNT Digital Library
Internal-Film Cooling of Rocket Nozzles
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 ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
Date:
June 8, 1948
Creator:
Sloop, J. L. & Kinney, George R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet
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.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet
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.
Object Type:
Report
System:
The UNT Digital Library
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
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.
Object Type:
Report
System:
The UNT Digital Library
Notes on Geared Tabs at Supersonic Speeds
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.
Object Type:
Report
System:
The UNT Digital Library
Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2
"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 with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed" (p. 1).
Date:
July 8, 1948
Creator:
Mottard, Elmo J. & Ruggles, Robert D.
Object Type:
Report
System:
The UNT Digital Library
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
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.
Object Type:
Report
System:
The UNT Digital Library
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
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 Mach numbers.
Date:
November 8, 1948
Creator:
Silsby, Norman S. & McKay, James M.
Object Type:
Report
System:
The UNT Digital Library
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)
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 characteristics in the region of a vertical tail are provided.
Date:
November 8, 1948
Creator:
Salmi, Reino J.
Object Type:
Report
System:
The UNT Digital Library
The effect of torsional flexibility on the rolling characteristics at supersonic speeds of tapered unswept wings
From Summary: "An analysis is presented of the effect of torsional flexibility on the rolling characteristics at supersonic speeds of tapered unswept wings with partial-span constant-percent-chord ailerons extending inboard from the wing tip. The geometric variables considered are aspect ratio, taper ratio, aileron span, and aileron chord. The shape of the wing-torsional-stiffness curve is assumed and the twisting moment is considered to result solely from the pressure distribution caused by aileron deflection, so that the necessity of using a successive-approximation method is avoided."
Date:
March 8, 1949
Creator:
Tucker, Warren A. & Nelson, Robert L.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance of AN-F-58 fuels in J33-A-21 single combustor
Report discussing three fuels conforming to AN-F-58 specification were investigated in order to determine the influence of boiling temperatures and aromatic content on altitude performance in single combustor of a 4600-pound-thrust turbojet engine.
Date:
April 8, 1949
Creator:
Dittrich, Ralph T. & Jackson, Joseph L.
Object Type:
Report
System:
The UNT Digital Library
Estimated transonic flying qualities of a tailless airplane based on a model investigation
Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date:
June 8, 1949
Creator:
Donlan, Charles J. & Kuhn, Richard E.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor
"An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6" (p. 1).
Date:
July 8, 1949
Creator:
Cook, William P. & Koch, Richard G.
Object Type:
Report
System:
The UNT Digital Library
Paper Chromatography in Synthetic Organic Chemistry: Microgram Scale Syntheses of Labeled Monoiodotyrosine, diiodotyrosine and thyroxine
A report on paper chromatography in synthetic organic chemistry.
Date:
July 8, 1949
Creator:
Lemmon, R. M.; Tarpey, Winifred & Scott, Kenneth G.
Object Type:
Report
System:
The UNT Digital Library
Progress Report: May 1949: Preparation of Ductile Zirconium
Report discussing progress made by the National Research Corporation regarding preparation of ductile zirconium during the month of May, 1949.
Date:
July 8, 1949
Creator:
DiPietro, W. O.; Findlay, G. R. & Mellen, G. L.
Object Type:
Report
System:
The UNT Digital Library
Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers
Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date:
July 8, 1949
Creator:
Hemenover, Albert D.
Object Type:
Report
System:
The UNT Digital Library
Analysis and Preliminary Investigation of Eddy-Current Heating for Icing Protection of Axial-Flow-Compressor Blades
From Introduction: "An analysis of eddy currents in a compressor blade, the geometry of which has been limited to that of a flat plate for simplicity, is presented."
Date:
August 8, 1949
Creator:
Dallas, Thomas & Ellisman, C.
Object Type:
Report
System:
The UNT Digital Library