National Advisory Committee for Aeronautics (NACA) - 173 Matching Results

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Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data

Description: Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date: August 9, 1955
Creator: Beckwith, Ivan E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin

Description: Report presenting testing of two 2024-T3 aluminum-alloy multiweb wing structures (MW-2 and MW-3), similar to airplane or missile wings, at a Mach number of 2 under simulated supersonic flight conditions. Results regarding experimentally determined test conditions, model temperatures, strain-gage results, and model failures are provided. The report indicates that much of the stress data does not agree with expected results, but there is too much uncertainty regarding the reduction of strain data… more
Date: August 9, 1955
Creator: Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes

Description: Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date: November 9, 1955
Creator: Sams, Eldon W. & Rom, Frank E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aircraft-Fuel-Tank Design for Liquid Hydrogen

Description: "Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than… more
Date: August 9, 1955
Creator: Reynolds, T. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor

Description: Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet te… more
Date: December 9, 1954
Creator: Butze, Helmut F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance

Description: Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date: July 9, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design

Description: Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stabilit… more
Date: November 9, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation

Description: Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
Date: March 9, 1953
Creator: Spooner, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System

Description: Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date: April 9, 1956
Creator: Scallion, William I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches

Description: Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date: April 9, 1953
Creator: Bihrle, William, Jr. & Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations

Description: "An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner f… more
Date: July 9, 1953
Creator: Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation Between Hydrogen Pressure and Protective Action of Additives in the Molten Sodium Hydroxide - Nickel System

Description: Memorandum presenting an investigation of the effect of various metallic additives on the molten sodium hydroxide - nickel system. The hydrogen evolved from such systems was measured and the evolution was correlated with the effect of the metal on mass transfer. Results regarding a check with standard tests, purging, presence of two valences for chromium, reaction time of the additive, and pressure within nickel crucibles are provided.
Date: February 9, 1956
Creator: May, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effectiveness of Inhibitors for Mass Transfer and Corrosion in Sodium Hydroxide - Nickel Systems

Description: Memorandum presenting static crucible tests with additions of the reducing agents sodium chromite Na(sub 3)CrO(sub 4) and manganese dioxide MnO(sub 2) indicate that salts soluble in sodium hydroxide may be added to inhibit mass transfer in nickel. The metals manganese, vanadium, and molybdenum were also investigated in static crucibles and found to be ineffective.
Date: February 9, 1956
Creator: Forestieri, Americo F. & Lad, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane

Description: Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.
Date: October 9, 1957
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electric Thrust Meter Suitable for Flight Investigation of Propellers

Description: A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date: May 9, 1949
Creator: Perkins, Porter J., Jr. & Millenson, Morton B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes

Description: From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date: November 9, 1955
Creator: Rom, F. E. & Sams, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations of Air-Cooled Turbine Rotors for Turbojet Engines 1: Experimental Disk Temperature Distribution in Modified J33 Split-Disk Rotor at Speeds up to 6000 RPM

Description: "An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation a… more
Date: January 9, 1952
Creator: Schramm, Wilson B. & Ziemer, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Description: Report discussing an investigation of the dynamic stability and control characteristics of a model of the Ryan X-13 jet VTOL airplane in hovering and transition flight. Flight control was smooth and easy without the gyroscopic effects of the engine represented, but adding a simulation of the gyroscopic effects caused the plane to become uncontrollable in hovering flight without artificial stabilization. The transition was found to be easy to perform with and without gyroscopic effects, but the … more
Date: September 9, 1958
Creator: Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall

Description: "A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number… more
Date: November 9, 1950
Creator: Davis, Don D., Jr. & Wood, George P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane With External Stores Installed

Description: Memorandum presenting a supplementary investigation in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement on the spin and spin-recovery characteristics of a scale model of the McDonnell F2H-3 airplane. Results regarding wing-tip tanks and experimental aerodynamic shapes are provided.
Date: June 9, 1952
Creator: Wilson, Jack H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Description: Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date: May 9, 1955
Creator: Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229

Description: Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date: December 9, 1947
Creator: King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Abstracts Pertaining to Seaplanes

Description: "About 500 additional references pertaining to hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings:GENERAL INFORMATION, HYDROSTATICS, HYDRODYNAMICS, AERODYNAMICS, OPERATION, and RESEARCH. The compilation is an extension of NACA RM No. L6I13, entitled "Abstracts Pertaining to Seaplanes," by Jerold M. Bidwell and Douglas A. King. An author index and a subject index are included" (p. 1).
Date: March 9, 1948
Creator: Bidwell, Jerold M. & King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static tests of a shrouded and an unshrouded propeller

Description: Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.
Date: February 9, 1948
Creator: Platt, Robert J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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