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NACA Research Memorandums
181
Atomic Energy Commission Reports
53
Hanford Works Reports
28
NACA Technical Reports
22
HW (Series)
20
University of California Radiation Laboratory Reports
19
Oak Ridge National Laboratory Reports
17
ORNL (Series)
11
UCRL (Series)
8
AEC research and development report
7
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361 Matching Results
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Analysis of Coaxial Two-Terminal Conical Capacitor
From Abstract: "The electric field is plotted and its construction steps for axial symmetry are given."
Date:
April 6, 1962
Creator:
Selby, M. C.
Object Type:
Report
System:
The UNT Digital Library
Tables of Electron Radial Functions and Tangents of Phase Shifts for Light Nuclei (Z=1 through 10)
From Introduction: "This Monograph, supplemented by ORNL-3207 [9], should eliminate completely the need for use of approximate formulas (e.g. those of Kotani and Ross [10]). The formulation of the problem has been summarized in sec. II. This is followed in sec. III by a discussion of the methods used in numerical calculations. Sec. IV contains a detailed explanation to facilitate the use of present tables."
Date:
August 6, 1964
Creator:
Bhalla, C. P.
Object Type:
Report
System:
The UNT Digital Library
Norfolk-Peninsula Area (ARMS-II)
From Introduction: "The ARMS-II Norfolk - Peninsula area survey was one many that have been flown for the CETO since the nationwide ARMS program was started (1958). Figure 2 shows the location of the areas that have been completed to date. The purpose of the program is to measure the present environmental levels of gamma radiation in areas around nuclear facilities and planned nuclear activities."
Date:
December 6, 1961
Creator:
Guillou, R. B.
Object Type:
Report
System:
The UNT Digital Library
Performance of Isentropic Nose Inlets at Mach Number of 5.6
Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all the configurations yielded larger total-pressure recoveries than had previously been obtained with a single-conical-shock inlet. Results regarding the flow about the forebody, inlet performance, and performance comparisons are provided.
Date:
May 6, 1954
Creator:
Bernstein, Harry & Haefeli, Rudolph C.
Object Type:
Report
System:
The UNT Digital Library
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61
Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6. Separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The configuration investigated simulated a heavy bomber airplane with a large store or nacelle with frontal area equivalent to a twin-engine nacelle.
Date:
July 6, 1955
Creator:
Smith, Norman F. & Carlson, Harry W.
Object Type:
Report
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant
Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
February 6, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
Object Type:
Report
System:
The UNT Digital Library
Static Longitudinal and Lateral Stability Characteristics Including Effects of Transonic Area Rule and Wing Modification of a 0.10- Scale Model of the Douglas A4D-1 Airplane at Transonic Speeds
Report discussing testing of a model of the Douglas A4D-1 to investigate the static longitudinal characteristics of wing and fuselage modifications and the static lateral characteristics of the basic model.
Date:
July 6, 1956
Creator:
Bollech, Thomas V. & Wornom, Dewey E.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine
Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2
Memorandum presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at a Mach number of 1.99 and a Reynolds number of 6.0 million. Testing was performed to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components. Results regarding the body-wing-tail combination, body, wing and tail, body-wing and body-tail combinations, and body-wing-tail interference are provided.
Date:
December 6, 1954
Creator:
Spahr, J. Richard
Object Type:
Report
System:
The UNT Digital Library
Transonic Wind-Tunnel Investigation of Static-Pressure Fluctuations in Duct of a Scale Inlet Model of a Supersonic Fighter-Bomber Airplane
Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.
Date:
August 6, 1957
Creator:
Brooks, Joseph D.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner
"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).
Date:
August 6, 1953
Creator:
von Glahn, U.
Object Type:
Report
System:
The UNT Digital Library
Flight Instrument for Measurement of Liquid-Water Content in Clouds at Temperatures Above and Below Freezing
"A principle formerly used in an instrument for cloud detection was further investigated to provide a simple and rapid means for measuring the liquid-water content of clouds at temperatures above and below freezing. The instrument consists of a small cylindrical element so operated at high surface temperatures that the impingement of cloud droplets creates a significant drop in the surface temperature. The instrument is sensitive to a wide range of liquid-water content and was calibrated at one set of fixed conditions against rotating multicylinder measurements. The limited conditions of the calibration Included an air temperature of 20 F, an air velocity of 175 miles per hour, and a surface temperature in clear air of 475 F" (p. 1).
Date:
March 6, 1951
Creator:
Perkins, Porter J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, TED No. NACA DE 327
Report presenting an investigation of a model of the Kingfisher XAUM-2 flying torpedo to determine the pressure recoveries within the jet engine nacelle and to determine the effects of several changes in model configuration on the aerodynamic characteristics of the model. The effectiveness of elevons and tabs as control devices was also investigated.
Date:
October 6, 1949
Creator:
Cocke, Bennie W. & Barnett, U. Reed
Object Type:
Report
System:
The UNT Digital Library
Static Longitudinal and Lateral Stability and Control Characteristics of an 0.065-Scale Model of the Chance Vought Regulus 2 Missile at Mach Numbers of 1.41, 1.61, and 2.01 Research Memorandum
Report discussing testing to determine the longitudinal and lateral stability and control characteristics of a Chance Vought Regulus II missile at several Mach and Reynolds numbers.
Date:
June 6, 1955
Creator:
Robinson, Ross B.; Driver, Cornelius & Spearman, M. Leroy
Object Type:
Report
System:
The UNT Digital Library
Effect of Fuel Injectors and Liner Design on Performance of an Annular Turbojet Combustor With Vapor Fuel
Memorandum presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5 inch diameter annular combustor which had been previously developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and the liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.
Date:
April 6, 1953
Creator:
Norgren, Carl T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the arming propeller, the effect of adding a spoiler nose ring to a basic model, and the effect of changes in the spin rate are provided.
Date:
July 6, 1954
Creator:
Bird, John D. & Lichtenstein, Jacob H.
Object Type:
Report
System:
The UNT Digital Library
Performance at Simulated High Altitudes of a Prevaporizing Annular Turbojet Combustor Having Low Pressure Loss
Memorandum presenting an investigation conducted to reduce the pressure drop in an experimental combustor designed to operate with high efficiencies at high altitude. The combustor utilized a previously designed prevaporizing fuel system that supplied vapor fuel to the injectors for high-altitude operation. Results regarding combustor development and performance of final combustor model 47L are provided.
Date:
December 6, 1956
Creator:
Norgren, Carl T.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of Air-turborocket Engine Performance Including Effects of Component Changes
Report presenting analytical estimates of the thrust, efficiency, drag, and weight of the air-turborocket engine. The effects of changes in the engine components on design and off-design performance are emphasized. Results regarding the performance, effect of design parameters, effect of subsonic cruising Mach number, geometry variations, engine weight estimates, and comparison with turbojet engines are provided.
Date:
April 6, 1956
Creator:
Luidens, Roger W. & Weber, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0
Report presenting an investigation of an all-internal conical compression inlet with annular bleed at the throat at Mach number 5.0 and zero angle of attack. Results regarding the performance of the diffuser alone, a Pitot-pressure survey of the flow leaving the diffuser, total-pressure distribution, and inlet efficiencies are provided.
Date:
August 6, 1958
Creator:
Stitt, Leonard E. & Obery, Leonard J.
Object Type:
Report
System:
The UNT Digital Library
Dynamic Lateral Behavior of High-Performance Aircraft
Memorandum presenting several proposed-high performance aircraft that have been studied analytically and by model flight tests to define some problem areas in dynamic lateral behavior of high-speed aircraft which require specific attention. Aileron control problems and Dutch roll characteristics with and without artificial damping were considered.
Date:
August 6, 1958
Creator:
Moul, Martin T. & Paulson, John W.
Object Type:
Report
System:
The UNT Digital Library
Electrical Techniques for Compensation of Thermal Time Lag of Thermocouples and Resistance Thermometer Elements
Note presenting a description of basic electrical networks that compensate for the thermal time lag of thermocouple and resistance thermometer elements used in combustion research and in the control of jet power plants. The measurement or the detection of rapid temperature changes by use of such elements can thereby be improved.
Date:
May 6, 1952
Creator:
Shepard, Charles E. & Warshawsky, Isidore
Object Type:
Report
System:
The UNT Digital Library
The Effect of Blade-Section Camber on the Stall-Flutter Characteristics of Three NACA Propellers at Zero Advance
Report presenting an investigation to determine the effect of blade-section camber on the stall-flutter characteristics of three propellers using a 6000-horsepower propeller dynamometer. Up to a certain blade angle, there was an increase in flutter-speed coefficient with an increase in blade-section design lift coefficient. An increase in thrust was found to lead to an increase in tip Mach number in the flutter region of the propeller blades.
Date:
April 6, 1953
Creator:
Allis, Arthur E. & Swihart, John M.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness
From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the conventional section in transonic speed range."
Date:
November 6, 1947
Creator:
Eggers, A. J., Jr.
Object Type:
Report
System:
The UNT Digital Library
A fuel-distribution control for continuous-flow manifold injection on reciprocating engines
"A fuel-distribution control for continuous-flow manifold injection on reciprocating engines is described. A method is installation of the control on an engine is suggested. The device controlled the flow to four spring-loaded nozzles within 2 percent of perfect distribution over a wide range of fuel-flow rates and the distribution was practically unaffected by uneven discharge-nozzle pressures" (p. 1).
Date:
June 6, 1947
Creator:
Gold, Harold & Straight, David M.
Object Type:
Report
System:
The UNT Digital Library