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Technical Report Archive and Image Library
229
National Advisory Committee for Aeronautics Collection
147
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69
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62
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58
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Stability of Florothene Under Exposure to Gamma Radiation
The stability of fluorothene (polytrifluorochloroethylene, Kel-F) to gamma radiation has been investigated to estimate the probable life expectancy of fluorothene equipment exposed to Purex process solutions. Samples of fluorothene were exposed to total gamma radiation dosages up to 10 degree R. The results of these tests substantiate the findings reported by Sisman and Bopp in their compilation of data on the affects of radiation on plastics.
Date:
July 6, 1956
Creator:
Adler, K. L.
Object Type:
Report
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at Low Speed on a Canard Missle During Simulated Launching From the Midsemispan and Wing-Tip Locations of a 45 Degree Sweptback Wing-Fuselage Combination
Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.
Date:
April 6, 1955
Creator:
Alford, William J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Clarification of Redox Dissolver Solution by Centrifugation with Scavenger
From statement of objectives: The purposes of the work described in this report are to provide data useful for designing and operating the dissolver solution clarification equipment to be installed in the Redox production plant.
Date:
June 6, 1950
Creator:
Allen, A. W.
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
Preliminary report on human excretion of tritium
Six subjects received a few millicuries Of tritium by inhalation of isotopically labeled hydrogen gas. The concentration of H{sup 3} in the urine of these individuals has been followed for a period of some 15 days. The rate of excretion of the tritium was found to be constant for a given subject but to vary considerably, among individuals. Data on five individuals arbitrarily normalized to coincide at zero time showed a range in biological half-life from about 9 days to nearly 13 days. These values are to be compared with the value calculated for the Chalk River ``Standard Man`` of 13.5 days, assuming the tritim to be confined to the body water.
Date:
April 6, 1950
Creator:
Anderson, E.C. & Pinson, E.
Object Type:
Report
System:
The UNT Digital Library
Enclosure Pressure Calculation Method
A method of determining enclosure pressure in the event of a reactor rupture is presented and a sample calculation is shown. This method was used in calculating the design pressure of the Dresden Nuclear Power Station enclosure.
Date:
October 6, 1956
Creator:
Bailey, J. A.
Object Type:
Report
System:
The UNT Digital Library
Flight and Preflight Tests of a Ram Jet Burning Magnesium Slurry Fuel and Utilizing a Solid-Propellant Gas Generator for Fuel Expulsion
Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.
Date:
April 6, 1955
Creator:
Bartlett, Walter A., Jr. & Hagginbothom, William K., Jr.
Object Type:
Report
System:
The UNT Digital Library
Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques
Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.
Date:
November 6, 1951
Creator:
Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
A Large Bakeable Vacuum Valve
This report describes the development and design of a large bakeable valve that is based on a unique seat arrangement and a novel motion seal.
Date:
August 6, 1959
Creator:
Batzer, Thomas H.
Object Type:
Report
System:
The UNT Digital Library
Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20
Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.
Date:
December 6, 1954
Creator:
Bellman, Donald R. & Murphy, Edward D.
Object Type:
Report
System:
The UNT Digital Library
Effect of channel geometry on the quenching of laminar flames
Report presenting the effect of channel geometry on flame quenching, as calculated on the basis of average active particle chain lengths, is related among six different geometries: plane parallel plates of infinite extent, cylindrical tubes, rectangular slots, cylindrical annuli, and tubes of elliptical and equilaterally triangular shape. The results indicated that the observed variation of flame quenching as a function of quenching geometry may be successfully predicted for a range of pressures and for rich as well as lean propane-air flames.
Date:
May 6, 1954
Creator:
Berlad, A. L. & Potter, A. E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Pressure Recovery of a Single-Conical-Shock Nose Inlet at Mach Number 5.4
An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.
Date:
April 6, 1953
Creator:
Bernstein, Harry & Haefeli, Rudolph C.
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
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 of the configurations yielded larger total-pressure recoveries than had previously been obtianed with a single-conical-shock inlet. Results regarding the flow about the forebody and performance comparisons are provided.
Date:
May 6, 1954
Creator:
Bernstein, Harry & Haefeli, Rudolph C.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the pressure-ratio requirements of the Langley 11-inch hypersonic tunnel with a variable-geometry diffuser
Report presenting tests in the 11-inch hypersonic tunnel at Mach number 6.86 to determine the effectiveness of an adjustable supersonic diffuser without boundary-layer control in reducing the pressure ratios across the system required to maintain supersonic flow. Testing indicated that the pressure ratio could be reduced to about one-third the pressure ratio required for starting.
Date:
October 6, 1950
Creator:
Bertram, Mitchel H.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Safety Analysis of the Sodium-Deuterium Reactor (SDR)
From abstract: This work is a safety analysis of the preliminary design of a nuclear reactor.
Date:
March 6, 1959
Creator:
Beusman, Curtis C. & Bernsohn, E.
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
Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
Report presenting an investigation made in the stability tunnel to determine the effectiveness with which the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket could be studied by a free-oscillation technique and to study certain peculiarities of behavior. Results regarding the stability of the original model, effect of reversing direction of the arming propeller, effect of increasing size of reversed-rotation of the arming propeller, effect of removing the arming propeller, effect of adding a spoiler nose ring to the basic model, and the effect of changes in spin rate are provided.
Date:
July 6, 1954
Creator:
Bird, John D. & Lichtenstein, Jacob H.
Object Type:
Report
System:
The UNT Digital Library
Chemical Development Status Report for Week Ending June 1, 1956
This report talks about Chemical Development Status Report for Week Ending June 1, 1956
Date:
June 6, 1956
Creator:
Blanco, R. E. & Ferguson, D. E.
Object Type:
Report
System:
The UNT Digital Library
Stability and drag characteristics of 1/10-scale model of the Convair XF2Y-1 airplane with open inlets containing boundary layer splitter plates as obtained in free flight at Mach numbers between 0.7 and 1.5: TED No. NACA DE 365
Report presenting a scale rocket-propelled model of the Convair XF2Y-1 water-based fighter airplane in free flight in a range of Mach numbers. Results regarding stability characteristics, trim characteristics, drag characteristics, and inlet and duct characteristics are provided.
Date:
April 6, 1955
Creator:
Bland, William M., Jr.
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
Experimental Investigation of Internal Flow Characteristics of Forward Underslung Fuselage Scoops With Unswept Entrances at Mach Numbers of 1.41 to 1.96
Report presenting an investigation of two versions of a type of forward underslung scoop mounted on a pointed fuselage in the supersonic blowdown tunnel. The scoop entrances were in the shape of a 60 degree sector of an annulus, but the sides of one scoop were sweptback, while the others were unswept. Results regarding the shadowgraphs and surface-pressure distributions and total-pressure recovery are provided.
Date:
March 6, 1952
Creator:
Boswinkle, Robert W., Jr. & Mitchell, Meade H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Pressure and Force Characteristics at Transonic Speeds of a Submerged Divergent-Walled Air Inlet on a Body of Revolution
Report presenting an investigation in the transonic tunnel on a submerged inlet with a divergent-walled approach ramp to determine flow phenomena, pressure recovery, and external forces to provide correlation with available data obtained on similar inlets. Results regarding the pressure characteristics, aerodynamic forces, and performance comparisons are provided.
Date:
May 6, 1953
Creator:
Braden, John A. & Pierpont, P. Kenneth
Object Type:
Report
System:
The UNT Digital Library
Health-Physics Monthly Information Report. October 1951
None
Date:
December 6, 1951
Creator:
Bradley, J. E. & Burbage, J. J.
Object Type:
Report
System:
The UNT Digital Library