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NACA Research Memorandums
148
Atomic Energy Commission Reports
34
Hanford Works Reports
14
University of California Radiation Laboratory Reports
11
HW (Series)
10
NACA Technical Reports
8
BMI (Series)
7
Battelle Memorial Institute Reports
7
Oak Ridge National Laboratory Reports
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Investigation of effect of span and spanwise location of plain and stepped spoiler ailerons on lateral control characteristics of a wing with leading edge swept back 51.3 degrees
Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of a 51.3 degree sweptback-wing model equipped with either plain or stepped spoiler ailerons with a fixed projection of 5-percent-wing chord and various spans and spanwise locations. The results indicated that spanwise rolling-effectiveness charts of flap-type ailerons can not be used to predict effectiveness of spoiler-type ailerons on swept wings. Results regarding the wing aerodynamic characteristics with spoiler ailerons retracted, wing aerodynamic characteristics with spoiler ailerons projected, and a comparison of spoiler-type and flap-type ailerons.
Date:
January 18, 1950
Creator:
Fischel, Jack & Hammond, Alexander D.
Object Type:
Report
System:
The UNT Digital Library
Comparison of "Staggered" and "Split-Flow" Air Cooling Systems
The following report follows an investigation comparing "staggered" and "spit-flow" air cooling systems.
Date:
April 18, 1950
Creator:
Winsche, Warren E.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions
A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eight radial stations of the NACA 10-(5)(066)-03 propeller.
Date:
April 18, 1950
Creator:
Evans, Albert J. & Luchuk, Wallace
Object Type:
Report
System:
The UNT Digital Library
Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail
Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."
Date:
May 18, 1950
Creator:
Fisher, Lloyd J. & Tarshis, Robert P.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(0)(066)-03 Propeller Under Operating Conditions
The fifth report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(0)(066)-03 propeller.
Date:
May 18, 1950
Creator:
Steinberg, Seymour & Milling, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines
From Introduction: "An analytical investigation of the problems arising in connection with this cooling method was conducted at the NACA Lewis laboratory and is presented herein. This analysis investigates: (1) the smallest diameter hole that can be made without endangering the circulation of the liquid, and (2) methods of improving the circulation in a small-diameter hole."
Date:
July 18, 1950
Creator:
Eckert, E. R. G. & Jackson, Thomas W.
Object Type:
Report
System:
The UNT Digital Library
Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method
Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high speed 7- by 10-foot tunnel to determine the lateral-control characteristics of a semispan wing-fuselage combination equipped with flap-type and spoiler-type controls. Both the flap-type and spoiler-type controls provide lateral control through the Mach number range investigated.
Date:
July 18, 1950
Creator:
Hammond, Alexander D.
Object Type:
Report
System:
The UNT Digital Library
The Potential of the Pu(III)-Pu(IV) Couple: The Hydrolysis Constant of Pu(IV)
Report discussing an experiment in which the formal potentials of the Pu(III)-Pu(IV) couple in 1M perchloric acid and in 1M hydrochloric acid are determined. The potentials were measured through potentiometric titrations of Pu(III).
Date:
July 18, 1950
Creator:
Rabideau, Sherman W.; Lemons, Joe F. & Rollefson, G. K.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Performance Data on General Electric Integrated Electronic Control Operating on J47 RX1-3 Turbojet Engine in NACA Altitude Wind Tunnel
From Summary: "Performance data obtained with recording oscillographs are presented to show the transient response of the General Electric Integrated Electronic Control operating on the J47 RXl-3 turbo-Jet engine over a range of altitudes from 10,000 to 45,000 feet and at ram pressure ratios of 1.03 and 1.4. These data represent the performance of the final control configuration developed after an investigation of the engine transient behavior in the NACA altitude wind tunnel. Oscillograph traces of controlled accelerations (throttle bursts), controlled decelerations (throttle chops), and controlled altitude starts are presented."
Date:
July 18, 1950
Creator:
Blivas, Darnold & Taylor, Burt L., III
Object Type:
Report
System:
The UNT Digital Library
Properties of Neutralized and Concentrated Aqueous Waste - Low Acid Flowsheets TBP-HW-No. 4 and No. 5
This report discusses properties and data regarding the neutralized and concentrated aqueous waste produced during studies of the tributyl phosphate (TBP) solvent extraction process.
Date:
July 18, 1950
Creator:
Curtis, M. H.; Harmon, M. K. & Cooper, V. R.
Object Type:
Report
System:
The UNT Digital Library
The transonic characteristics of a low-aspect-ratio triangular wing with a constant-chord flap as determined by wing-flow tests, including correlation with large-scale tests
Report presenting wing-flow-method measurements for 0.47 to 1.15 Mach number of the longitudinal-stability and -control characteristics of a triangular wing of aspect ratio 2 equipped with a constant-chord flap. Changes in the lift-curve slope and aerodynamic-center position through the transonic speed range were moderate and gradual. Results regarding triangular-wing characteristics, flap characteristics, and a comparison of the wind-tunnel and free-flight-test results at higher Reynolds numbers are provided.
Date:
August 18, 1950
Creator:
Rathert, George A., Jr.; Rolls, L. Stewart & Hanson, Carl M.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation at Mach numbers of 2.0 and 2.9 of several configurations of a supersonic ram-jet test vehicle
Report presenting wind-tunnel tests at Mach numbers of 2.0 and 2.9 to investigate the aerodynamic characteristics of several configurations of a supersonic ram-jet test vehicle. Three low-aspect-ratio wing configurations, with the ram-jet engine located forward and below the wing, were tested in pitch at Mach number 2.0.
Date:
August 18, 1950
Creator:
Spahr, J. Richard & Robinson, Robert A.
Object Type:
Report
System:
The UNT Digital Library
A Design for a Rotary Reactivity Control for a Test Reactor
Tests made on the Oy-Tu reacting assembly at Pajarito indicate that the lateral displacement of two halves of the active material within the assembly can be used as a control mechanism on this type of reacting assembly. This report describes a reacting assembly using a rotary control mechanism based on this principle and indicates the sensitivity of control possible with such a device.
Date:
September 18, 1950
Creator:
Josephson, V. (Vernal)
Object Type:
Report
System:
The UNT Digital Library
Evaluation of the Pentaether and Chelate Processes for the Chemical Separation of Plutonium and Uranium
Research at the University of California Radiation Laboratory has been directed toward the development of processes designed to recover plutonium and uranium from neutron-irradiated uranium. This report has been prepared in answer to requests for information by interested workers in the Atomic Energy programs. The material discussed herein represents the efforts of a sizable research group over several years, and summarizes both the current status of the investigation and the future program now contemplated.
Date:
September 18, 1950
Creator:
Hicks, T. E. & Crandall, Howard William, 1921-1990
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation at Mach Numbers From 0.8 to 1.4 to Determine the Zero-Lift Drag of Wings With 'M' and 'W' Plan Forms
Report presenting testing of the zero-lift drag of two wings, one with 45 degree sweepforward of the inboard panel and 45 degree sweepback of the outboard panel ("M" wing) and the other with a reverse sweep ("W" wing) at a range of Mach numbers. Both wings were found to have greater drag than a sweptback wing and less drag than a rectangular wing at transonic speeds. The differences were reduced at Mach numbers above 1.25.
Date:
September 18, 1950
Creator:
Katz, Ellis; Marley, Edward T. & Pepper, William B.
Object Type:
Report
System:
The UNT Digital Library
Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull-Up at a Mach Number of 0.96
"Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up to an airplane normal-force coefficient of 0.91 at a Mach number of approximately 0.96" (p. 1).
Date:
September 18, 1950
Creator:
Carner, H. Arthur & Payne, Mary M.
Object Type:
Report
System:
The UNT Digital Library
Multiplying Lattices
The use of thermally fissionable material in the lattice adds a distributed source of fast neutrons which must be considered in evaluating the problem.
Date:
October 18, 1950
Creator:
Brown, H.
Object Type:
Report
System:
The UNT Digital Library
NACA research on combustors for aircraft gas turbines 1: effects of operating variables on steady-state performance
Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed. Trends depicting the effect of inlet-air pressure, temperature, and velocity and fuel-air ratio on performance characteristics, such as combustion efficiency, maximum temperature rise attainable, pressure loss, and combustor-outlet temperature distribution are described for a variety of turbojet combustors of the liquid-fuel type. These trends are further discussed as effects significant to the turbojet engine, such as altitude operational limits, specific fuel consumption, thrust, acceleration, and turbine life.
Date:
October 18, 1950
Creator:
Olson, Walter T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
The Corrosion of Miniature Fuel Plates in Simulated Reactor Cooling Water
Technical report issued as one of a series of reports concerned with corrosion studies for the Materials Resting Reactor, created to both determine the effect of various practices for fuel plate fabrication on corrosion resistance and to determine the extent of penetration of the fuel plates by localized corrosion attack. [From Introduction]
Date:
December 18, 1950
Creator:
English, James L.
Object Type:
Report
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane
"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made" (p. 1).
Date:
December 18, 1950
Creator:
Berman, Theodore
Object Type:
Report
System:
The UNT Digital Library
Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration
Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date:
December 18, 1950
Creator:
Becht, Robert E.
Object Type:
Report
System:
The UNT Digital Library
The Synthetic Liquid Fuel Potential of Nevada
Report documenting the suitability of Nevada for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.
Date:
December 18, 1950
Creator:
Ford, Bacon, and Davis
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device
Report presenting the effectiveness of a 50-percent-semispan, constant-percent-chord elevon, and of upper-space spoilers as lateral control surfaces for a wing-fuselage combination with a wing swept back 63 degrees over a range of Mach numbers. For the elevon, results indicated that only about half of the predicted rolling-moment effectiveness was realized. The spoilers were found to be inferior to the elevons for lateral control because of a rapid loss of effectivness above an angle of attack of 4 degrees.
Date:
January 18, 1951
Creator:
Olson, Robert N. & Mead, Merrill H.
Object Type:
Report
System:
The UNT Digital Library
Methods for Connection to Revolving Thermocouples
Memorandum presenting several new methods that have been designed for obtaining electrical connection to thermocouples that are revolving at high speeds. Two general types of pickup system are described with modifications for special installations. Both pickup systems have been proved to transmit an accurate signal from a revolving thermocouple to within 0.045 millivolt at contact sliding speeds up to 5400 feet per minute.
Date:
January 18, 1951
Creator:
Tarr, Philip R.
Object Type:
Report
System:
The UNT Digital Library