Collection
Technical Report Archive and Image Library
101
National Advisory Committee for Aeronautics Collection
57
Office of Scientific & Technical Information Technical Reports
31
TRAIL Microcard Collection
28
Texas Attorney General Opinions
6
Government Documents A to Z Digitization Project
2
USDA Farmers' Bulletins
2
Texas State Publications
1
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NACA Research Memorandums
42
NACA Technical Notes
15
Atomic Energy Commission Reports
11
United States Geological Survey Reports
9
Los Alamos National Laboratory Reports
8
Trace elements investigations report
7
University of California Radiation Laboratory Reports
5
North American Aviation Reports
4
ANL (Series)
2
Argonne National Laboratory Reports
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141 Matching Results
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Minimum-drag ducted and pointed bodies of revolution based on linearized supersonic theory
Report presenting the linearized drag integral for bodies of revolution at supersonic speeds in a double-integral form which is not based on slender-body approximations but which reduces to the usual slender-body expression in the proper limit. The minimum-external-wave-drag problem is solved for a transition section connecting to two semi-infinite cylinders.
Date:
May 1954
Creator:
Parker, Hermon M.
Object Type:
Report
System:
The UNT Digital Library
Evaluation of the accuracy of an aircraft radio altimeter for use in a method of airspeed calibration
Report presenting an evaluation of an aircraft radio altimeter for use in a method of airspeed calibration differing from the radar-photothedolite method of a previous study only in that the geometric altitude is obtained from an aircraft radio altimeter. The accuracy and airspeed calibrations for the two methods were found to be similar.
Date:
May 1954
Creator:
Thompson, Jim Rogers & Kurbjun, Max C.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of heat-transfer and fluid-friction characteristics of white fuming nitric acid
Report presenting experiments conducted as part of the general rocket-research program to determine the heat-transfer and fluid-friction characteristics of white fuming nitric acid over a specific set of conditions.
Date:
May 1954
Creator:
Reese, Bruce A. & Graham, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Manual of the ICAO Standard Atmosphere Calculations by the NACA
Note presenting tables and figures of a standard atmosphere based on the Manual of the ICAO Standard Atmosphere. Detailed tables of pressures and densities are given for altitudes up to 20,000 meters and to 65,000 feet.
Date:
May 1954
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Role of Triple Collisions in Excitation of Molecular Vibrations in Nitrous Oxide
Note presenting an investigation of the importance of triple collisions in the thermal relaxation process of gaseous mixtures. Results of the experiments have shown that the thermal relaxation times of the gas mixtures studied can be very well explained on the basis of binary collisions alone and that triple collisions do not play a discernible part in the excitation of molecular vibrations.
Date:
May 1954
Creator:
Walker, Richard A.; Rossing, Thomas D. & Legvold, Sam
Object Type:
Report
System:
The UNT Digital Library
Evaluation of Alloys for Vacuum Brazing of Sintered Wrought Molybdenum for Elevated-Temperature Applications
Note describing the preparation and evaluation of 25 binary and ternary alloys with liquidus temperatures in the range of 2000 to 2500 degrees Fahrenheit as part of an investigation of potential brazing alloys for molybdenum for use at elevated temperatures. Three commercial alloys were also investigated.
Date:
May 1954
Creator:
Dike, Kenneth C.
Object Type:
Report
System:
The UNT Digital Library
Downwash characteristics and vortex-sheet shape behind a 63 degree swept-back wing-fuselage combination at a Reynolds number of 6.1 x 10(exp 6)
Report presenting an experimental investigation to define the downwash field and vortex-sheet shape behind a large-scale wing-fuselage combination with a 63 degree sweptback wing of aspect ratio 3.5. At positive angles of attack, the vortex sheet assumed a shape which initially bowed upward but flatten out downstream before the rolling-up process had occurred to an appreciable degree. Results regarding downwash data, shape and location of the vortex sheet, path of the vortex core, and comparison of theories with experimental results are provided.
Date:
May 1954
Creator:
Tolhurst, William H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wall interference in wind tunnels with slotted and porous boundaries at subsonic speeds
From Summary: "Linearized compressible-flow analysis is applied to the study of wind-tunnel-wall interference for subsonic flow in either two-dimensional or circular test sections having slotted or porous walls. Expressions are developed for evaluating blockage and lift interference."
Date:
May 1954
Creator:
Baldwin, Barrett S., Jr.; Turner, John B. & Knechtel, Earl D.
Object Type:
Report
System:
The UNT Digital Library
A theoretical investigation of the heating-up period of injected fuel droplets vaporizing in air
Report presenting an investigation of fuel injection into a combustion chamber, including theoretical and experimental results regarding the unsteady-state portion of the total vaporization time of single fuel droplets injected into air.
Date:
May 1954
Creator:
El Wakil, M. M.; Uyehara, O. A. & Myers, P. S.
Object Type:
Report
System:
The UNT Digital Library
Determination of lateral-stability derivatives and transfer-function coefficients from frequency-response data for lateral motions
Report presenting a method for determining the lateral-stability derivatives, transfer-function coefficients, and the modes for lateral motion from frequency-response data for a rigid aircraft. The method is based on the application of the vector technique to the equations of lateral motion, so that the three equations of lateral motion can be separated into six equations. Two numerical examples are given to demonstrate the use of the method.
Date:
May 1954
Creator:
Donegan, James J.; Robinson, Samuel W., Jr. & Gates, Ordway B., Jr.
Object Type:
Report
System:
The UNT Digital Library
A theoretical investigation of the aerodynamics of wing-tail combinations performing time-dependent motions at supersonic speeds
Report presenting a theoretical investigation of the contribution of horizontal tails to the lift and pitching moment due to angle of attack, a constant rate of pitch, and a constant vertical acceleration. Methods for calculating the flow fields behind wings with constant vertical acceleration are developed.
Date:
May 1954
Creator:
Martin, John C.; Diederich, Margaret S. & Bobbitt, Percy J.
Object Type:
Report
System:
The UNT Digital Library
Experimental Sea-Level Static Investigation of a Short Afterburner
Sea-level static testing of turbojet engine afterburner.
Date:
May 11, 1954
Creator:
Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
Object Type:
Report
System:
The UNT Digital Library
Some observations of shock-induced turbulent separation on supersonic diffusers
A survey of experimental data at supersonic speed indicated that shock-induced separation of a turbulent boundary layer will result for Mach numbers of approximately 1.33 or greater when a theoretical stream static-pressure-rise ratio of approximately 1.89 occurs across a shock interacting with the boundary layer. The significance of this tentative criterion for turbulent boundary-layer separation is discussed with respect to the design of supersonic diffusers.
Date:
May 4, 1954
Creator:
Nussdorfer, Theodore J.
Object Type:
Report
System:
The UNT Digital Library
Measurement and Calculation of Blade Torsional Deflection of Three Supersonic-Type Propellers
Report presenting an investigation to determine the blade torsional deflection of three supersonic-type propellers at various operating conditions. Blade-torsional deflection was found to produce appreciable results that can be predicted by theory with good accuracy. Results regarding the efficiency, thrust coefficient, and power coefficient are provided.
Date:
May 28, 1954
Creator:
Allis, Arthur E. & Foss, Willard E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a translating-cone inlet at Mach numbers from 1.5 to 2.0
Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel to evaluate the performance of a translating-cone inlet operated over a range of Mach numbers and angles of attack. The effects of spike projection and internal flow area variation on pressure recovery, external drag, and corrected air-flow variation were determined.
Date:
May 11, 1954
Creator:
Sterbentz, William H. & Leissler, L. Abbott
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
Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination
Report presenting an investigation in the transonic tunnel to determine the basic aerodynamic and loading characteristics of an unswept-wing-fuselage combination with a wing of aspect ratio 4, taper ratio 0.5, and NACA 65A004 airfoil sections. Force, moment, and pressure measurements were obtained for a range of Mach numbers and angles of attack.
Date:
May 24, 1954
Creator:
Hieser, Gerald; Henderson, James H. & Swihart, John M.
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 impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 1: performance of rotor alone
Report describing a supersonic-compressor rotor designed as an impulse-type with some deceleration along the tip and with turning to the axial direction. Results regarding the overall performance, inlet flow distribution, results of rotor-outlet surveys, blade element performance at 90 percent design speed, and blade element performance at open throttle are provided.
Date:
May 6, 1954
Creator:
Wilcox, Ward W.
Object Type:
Report
System:
The UNT Digital Library
Experimental Sea-Level Static Investigation of a Short Afterburner
Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.
Date:
May 11, 1954
Creator:
Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
Object Type:
Report
System:
The UNT Digital Library
Variation of Spontaneous Ignition Delays With Temperature and Composition for Propane-Oxygen-Nitrogen Mixtures at Atmospheric Pressure
Report presenting the ignition delays of propane-oxygen-nitrogen mixtures as a function of temperature and composition in a flow system. Results regarding the effect of apparatus parameters, effect of propane concentration, effect of oxygen concentration, effect of temperature, and interpretation in terms of slow reaction kinetics are provided.
Date:
May 4, 1954
Creator:
Jackson, Joseph L. & Brokaw, Richard S.
Object Type:
Report
System:
The UNT Digital Library
Low-velocity turning as a means of minimizing boundary-layer accumulations resulting from secondary flows within turbine stators
A study of a series of three single-passage nozzles, designed to turn the flow at different velocity levels but to identical outlet conditions, in order to determine whether secondary-flow accumulations of boundary-layer fluids within nozzles could be minimized by use of low-velocity turning. Results indicated that the type of turning with subsequent acceleration is highly effective in minimizing secondary-flow accumulations at the corner where the suction surface joins the end walls.
Date:
May 11, 1954
Creator:
Stewart, Warner L. & Wong, Robert Y.
Object Type:
Report
System:
The UNT Digital Library
Effects of Some Metal Additions on Properties of Molybdenum Disilicide
Memorandum presenting an investigation of the effect of the addition of approximately 6 percent nickel, cobalt, or platinum on some properties of molybdenum disilicide. These additions resulted in appreciably lowering the modulus-of-rupture strength from that of unalloyed molybdenum disilicide. Results regarding density and particle-size analysis, chemical analysis of bars, metallographic and x-ray analysis, density and resistivity, modulus-of-rupture strengths, thermal shock tests, and oxidation resistance are provided.
Date:
May 4, 1954
Creator:
DeVincentis, H. A. & Russell, W. E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the effects of profile shape on the aerodynamic and structural characteristics of thin, two-dimensional airfoils at supersonic speeds
Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.
Date:
May 7, 1954
Creator:
Katzen, Elliott D.; Kuehn, Donald M. & Hill, William A., Jr.
Object Type:
Report
System:
The UNT Digital Library