Resource Type
Serial/Series Title
NACA Research Memorandums
181
Atomic Energy Commission Reports
66
Hanford Works Reports
32
HW (Series)
27
NACA Technical Reports
25
University of California Radiation Laboratory Reports
24
Oak Ridge National Laboratory Reports
17
BNL (Series)
16
Brookhaven National Laboratory Reports
16
Report (U.S. Atomic Energy Commission)
13
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Mechanical Behavior of Crystalline Solids: Proceedings of a Symposium, April 28-29, 1962
From Introduction: "These first three chapters from a background of introduction and general ideas about dislocations. The next two chapters are concerned specifically with properties of ceramic materials, with emphasis on single crystals."
Date:
March 25, 1963
Creator:
United States. Bureau of Standards.
Object Type:
Report
System:
The UNT Digital Library
Climatic Charts and Data of the Radio Refractive Index for the United States and the World
From Introduction: "This Monograph has as its purpose the compilation and analysis of the extensive radio refractive index data available within the Central Radio Propagation Laboratory of the National Bureau of Standards. This will be accomplished by presenting both tabulations of basic data for specific locations and charts for interpolation to any location."
Date:
November 25, 1960
Creator:
Bean, B. R.; Horn, J. D. & Ozanich, A. M., Jr.
Object Type:
Report
System:
The UNT Digital Library
Progress Report on AEC Contract on Research and Development Program on Scintillation Crystals: Period 1 January 1956 to 1 April 1956
From Abstract: "This report covers the preliminary literature survey and the screening of activated cesium iodide and several alkali halides to qualitatively determine their luminerscence. The report also includes a proposal of the future work and a proposed budget for the 1957 fiscal year."
Date:
April 25, 1956
Creator:
Beadle, Robert
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01
Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date:
October 25, 1957
Creator:
Morris, Owen G. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From
"An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotless Aircraft Research Division by utilizing rocket-propelled test vehicles. No effects of mutual interference between the midspan spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared with the spoiler because of wing twisting" (p. 1).
Date:
February 25, 1952
Creator:
Strass, H. Kurt & Marley, Edward T.
Object Type:
Report
System:
The UNT Digital Library
A Summary of Results Obtained During Flight Simulation of Several Aircraft Prototypes With Variable-Stability Airplanes
Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.
Date:
May 25, 1956
Creator:
McNeill, Walter E. & Creer, Brent Y.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date:
August 25, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
Object Type:
Report
System:
The UNT Digital Library
A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes
Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.
Date:
February 25, 1958
Creator:
Setze, Paul C. & Nusbaum, William J.
Object Type:
Report
System:
The UNT Digital Library
De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding
Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date:
May 25, 1953
Creator:
Ruggeri, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Data on Rain Deflection from Aircraft Windshields by Means of High-Velocity Jet-Air Blast
From Summary: "A preliminary experimental investigation is being conducted to determine the feasibility of preventing rain from impinging on aircraft windshields by means of high-velocity jet-air blast. The results indicate that rain deflection by jet blast appears feasible for flight speeds comparable with landing and take-off speeds of interceptor-type jet aircraft; however, attainment of good visibility through the mist generated by raindrop breakup presents a problem. For the simulated windshield and the lower windshield angles used in the investigation, air-flow rates of the order of 3.3 pounds per minute of unheated air per inch of windshield span were required for adequate rain deflection at a free-stream velocity of 135 miles per hour."
Date:
July 25, 1955
Creator:
Ruggeri, Robert S.
Object Type:
Report
System:
The UNT Digital Library
A Photographic Study of Freezing of Water Droplets Falling Freely in Air
From Summary: "A photographic technique for investigating water droplets of diameter less than 200 microns falling freely in air at temperatures between 0 C and -50 C has been devised and used to determine: (1) The shape of frozen droplets, (2) The occurrence of collisions of partly frozen or of frozen and liquid droplets, and (3) The statistics on the freezing temperatures of individual free-falling droplets."
Date:
February 25, 1952
Creator:
Dorsch, Robert G. & Levine, Joseph
Object Type:
Report
System:
The UNT Digital Library
Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01
Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.
Date:
March 25, 1955
Creator:
Robinson, Ross B.
Object Type:
Report
System:
The UNT Digital Library
The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin
"Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).
Date:
October 25, 1956
Creator:
Buell, Donald A. & Tinling, Bruce E.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail
Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.
Date:
April 25, 1955
Creator:
Beam, Benjamin H.; Reed, Verlin D. & Lopez, Armando E.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of a Series of Practice Bombs
Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.
Date:
October 25, 1957
Creator:
Ward, Donald H.
Object Type:
Report
System:
The UNT Digital Library
Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis
"Model investigations were made to determine the ditching characteristics of three typical multiengine airplanes equipped with possible arrangements of hydro-ski ditching gear. The behavior of the models was determined from visual observations, acceleration records, and motion pictures of the landings. Data are presented in tabular form and sequence photographs" (p. 1).
Date:
April 25, 1950
Creator:
Fisher, Lloyd J.
Object Type:
Report
System:
The UNT Digital Library
Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6
Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.
Date:
January 25, 1955
Creator:
Henning, Allen B. & Brown, Clarence A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight Test of an End-Burning Solid-Fuel Ramjet
Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.
Date:
March 25, 1954
Creator:
Bartlett, Walter A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System
Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date:
June 25, 1958
Creator:
Smith, Arthur L. & Grobman, Jack S.
Object Type:
Report
System:
The UNT Digital Library
Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning
From Introduction: "Performance results of the tail-pipe burning investigation on the TG-180 turbojet engine and a comparison of experimental results with theoretical calculations are presented."
Date:
September 25, 1946
Creator:
Fleming, W. A. & Dietz, R. O.
Object Type:
Report
System:
The UNT Digital Library
Flight Observations of Aileron Flutter at High Mach Numbers as Affected by Several Modifications
Report presenting an investigation of aileron flutter associated with high-speed flight. When the aileron control system was modified by installing a hydraulic irreversible unit, it was possible to delay aileron flutter and reduce its amplitude. Results regarding the aileron flutter with and without the modifications, analysis of the time histories for the control systems, and relation between aileron upfloat and flutter are provided.
Date:
April 25, 1947
Creator:
Spreiter, John R.; Galster, George M. & Cooper, George E.
Object Type:
Report
System:
The UNT Digital Library
Preliminary evaluation of the performance of a uniflow two-stroke-cycle spark-ignition engine combined with a blowdown turbine and a steady-flow turbine
Report presenting calculations based on a theoretical analysis for a composite engine consisting of a uniflow two-stroke-cycle spark-ignition engine, a compressor, a blowdown turbine, and a steady-flow turbine. Operation of the engine is considered for four cases of gas mixtures and steady-flow turbine temperatures.
Date:
November 25, 1947
Creator:
Sather, Bernard I. & Foster, Hampton H.
Object Type:
Report
System:
The UNT Digital Library
Performance of a 20-inch steady-flow ram jet at high altitudes and ram-pressure ratios
Report presenting the results of an investigation conducted in the altitude wind tunnel to determine the performance of a 20-inch ramjet. The investigation was conducted at a range of altitudes and ram-pressure ratios using preheated 62-octane fuel. A net thrust of 8135 pounds educed to standard sea-level conditions, a net-thrust coefficient of 0.74, and an overall efficiency of 12.6 percent were attained at Mach number 1.845 at which the engine with a 5-foot combustion chamber was operated.
Date:
June 25, 1947
Creator:
Perchonok, Eugene; Sterbentz, William H. & Wilcox, Fred A.
Object Type:
Report
System:
The UNT Digital Library
An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane
From Introduction: "This report presents an analysis based on flight and wind-tunnel test data directed toward the determination of the probable cause of the pitch-up. Wing pressure distribution and stability and control characteristics in the dive are also included."
Date:
September 25, 1947
Creator:
Brown, Harvey H.; Rolls, L. Stewart & Clousing, Lawrence A.
Object Type:
Report
System:
The UNT Digital Library