Resource Type
Serial/Series Title
NACA Research Memorandums
184
Atomic Energy Commission Reports
50
NACA Technical Reports
33
Hanford Works Reports
26
HW (Series)
17
Oak Ridge National Laboratory Reports
17
University of California Radiation Laboratory Reports
17
UCRL (Series)
11
National Bureau of Standards Reports
8
CF (Series)
7
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The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane
Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date:
December 17, 1954
Creator:
Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket
Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.
Date:
June 17, 1952
Creator:
Abramson, Andrew E.
Object Type:
Report
System:
The UNT Digital Library
Interim Report on Corrosion by Zirconium-Base Fluorides
Report issued by the Oak Ridge National Laboratory discussing studies conducted on corrosion by fluorides. Equipment, procedures, results, and analysis is presented. This report includes tables, illustrations, and photographs.
Date:
January 17, 1961
Creator:
Adamson, G. M.; Crouse, R. S. & Manly, W. D.
Object Type:
Report
System:
The UNT Digital Library
Army Gas-Cooled Reactor Systems Program Semiannual Progress Report: January 1 - June 30, 1962
Report documenting the progress of the Army Gas-Cooled Reactor Systems Program to develop a mobile, low-power, nuclear power plant for Military field operation.
Date:
August 17, 1962
Creator:
Aerojet-General Corporation
Object Type:
Report
System:
The UNT Digital Library
Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed
Symbols and definition of various airspeed terms that have been adopted as standard by the NACA subcommittee on aircraft structural design are presented. The equations, charts, and tables required in the evaluation of true airspeed, calibrated airspeed, equivalent airspeed, impact and dynamic pressures, and Mach and Reynolds numbers have been compiled. Tables of the standard atmosphere to an altitude of 65,000 feet and a tentative extension to an altitude of 100,000 feet are given along with the basic equations and constants on which both the standard atmosphere and the tentative extension are based.
Date:
July 17, 1946
Creator:
Aiken, William S., Jr.
Object Type:
Report
System:
The UNT Digital Library
Horizontal-Tail Parameters as Determined From Flight-Test Tail Loads on a Flexible Swept-Wing Jet Bomber
Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.
Date:
January 17, 1957
Creator:
Aiken, William S., Jr. & Fisher, Raymond A.
Object Type:
Report
System:
The UNT Digital Library
Reaction of Hydrogen With Uranium
Report discussing reaction of hydrogen with uranium in a range of temperatures and pressures. Experimental materials, methods and results are included.
Date:
February 17, 1955
Creator:
Albrecht, William M. & Mallett, Manley William, 1909-
Object Type:
Report
System:
The UNT Digital Library
Polarographic Analysis of UNH in the IAW Stream
The following report describes two rapid, micro methods for the determination of UNH in Redox waste samples that had been developed fir the concentration range 0.2 to 100 g/l.
Date:
January 17, 1949
Creator:
Alkire, G. J. & Carson, W. N.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics: transonic bump method
Report presenting the results of an experimental investigation of the downwash and longitudinal stability characteristics of a semispan, triangular-wing airplane model with a horizontal tail. Lift, drag, and pitching-moment data re presented for the wing-fuselage combination. Results indicated that the model with the tail on or below the wing-chord plane possessed satisfactory stability characteristics throughout the test range of lift coefficient.
Date:
August 17, 1951
Creator:
Allen, Edwin C.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0
Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.
Date:
September 17, 1957
Creator:
Anderson, Arthur A. & Weinstein, Maynard I.
Object Type:
Report
System:
The UNT Digital Library
A High Volume Casting Furnace for Plutonium
A high-vacuum casting furnace with an internal diameter of 15 inches has been designed, fabricated, and installed at LASL. The furnace was designed to accommodate casting crucibles up to 7 inches OD; however with a larger diameter heating element, casting crucibles up to 9 inches could be accommodated. This report describes the basic features of the furnace and presents engineering drawings of both the furnace and the furnace box.
Date:
February 17, 1953
Creator:
Anderson, J. W. & Thomas, R. L.
Object Type:
Report
System:
The UNT Digital Library
Electronic Devices for Nuclear Physics: November 1, 1955 - January 31, 1956
Report regarding the ongoing development of both multi-alkali photocathodes and improved photomultipliers.
Date:
February 17, 1956
Creator:
Anderson, R. H.; Fowler, G. O.; Greenblatt, M. H. & Sommer, A. H.
Object Type:
Report
System:
The UNT Digital Library
The experimental and calculated characteristics of 22 tapered wings
From Summary: "The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experimentally determined airfoil section data. In general, the experimental and calculated characteristics are in sufficiently good agreement that the method may be applied to many problems of airplane design."
Date:
November 17, 1937
Creator:
Anderson, Raymond F.
Object Type:
Report
System:
The UNT Digital Library
A Spectrophotometric Determination of Mixtures of Hexavalent and Tetravalent Tuballoy : Preliminary Report
Report outlining a study that tested the use of colorimetric methods with high concentration phosphoric acid as a solvent for rapid analysis of mixtures of T^+4 and T^+6.
Date:
February 17, 1945
Creator:
Andrews, L. J.; Schaap, Ward B. & Gates, J. W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane
Report discussing testing of a Douglas D-558-II to investigate its longitudinal stability characteristics in accelerated flight at supersonic speeds. Information about the normal-force coefficients and their relation to stability and pitch-up of the aircraft is included.
Date:
February 17, 1954
Creator:
Ankenbruck, Herman O.
Object Type:
Report
System:
The UNT Digital Library
Lateral Motions Encountered with the Douglas D-558-II All-Rocket Research Airplane During Exploratory Flights to a Mach Number of 2.0
Memorandum presenting flight tests performed with the Douglas D-558-II research airplane in order to determine the lateral handling characteristics in straight flight at supersonic speeds. It primarily describes the lateral motions obtained at moderate and low angles of attack during a preliminary survey in pushovers and straight flight at supersonic Mach numbers up to about 2.0 at altitudes between 50,000 and 70,000 feet.
Date:
December 17, 1954
Creator:
Ankenbruck, Herman O. & Wolowicz, Chester H.
Object Type:
Report
System:
The UNT Digital Library
Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds
Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.
Date:
January 17, 1956
Creator:
Arabian, Donald D.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors
Memorandum presenting a preliminary and theoretical investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors for incompressible flow. A theoretical investigation was used to determine proper velocity diagrams and then the wake of a 1/4-inch-diameter rod was measured upstream of the rotor. The tests indicated that the derived equation will estimate the downstream distortion with reasonable accuracy for inlet total-pressure distortion which extends far enough circumferentially to alter the static-pressure field in the blade passage.
Date:
April 17, 1957
Creator:
Ashby, George C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Transonic Investigation of an Axial-Flow Compressor Rotor With a Contracted Exit Annulus
Report presenting an investigation of an axial-flow compressor rotor with a 13-percent reduction in exit annulus in Freon-12 gas at a range of tip speeds. In order to analyze the results caused by the reduction, the performance of the rotor was compared to that of the same rotor with a constant annular area. Results regarding the overall performance, radial variation of performance, and blade-element performance are also provided.
Date:
February 17, 1958
Creator:
Babington, Robert S.
Object Type:
Report
System:
The UNT Digital Library
A simplified theoretical method of determining the characteristics of a lifting rotor in forward flight
Theoretical derived expressions for the flapping, the thrust, the torque, and the profile drag-lift ratio of nonfeathering rotor with hinged, rectangular, linearly twisted blades are given as simple functions of the inflow velocity and the blade pitch. Representative values of the coefficients of each of the terms in these expressions are tabulated for a series of specified values of the tip-speed ratio. Analysis indicates that the tabulated values can be used to calculate, with reasonable accuracy, the characteristics of any rotor of conventional design.
Date:
March 17, 1941
Creator:
Bailey, F. J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Study of EOCR Modifications for Testing Fast Reactor Fuels
Report issued by the APDA over studies conducted on "methods for increasing the power generation in a fast reactor fuel element test sample" (p. 9). The methods investigated are presented and discussed. This report includes tables, and illustrations.
Date:
February 17, 1964
Creator:
Ball, G.; DeFelice, J.; Edwards, J. J.; Jens, W. H.; Kovac, L. R.; Poggi, R. et al.
Object Type:
Report
System:
The UNT Digital Library
Loop-Type Liquid-Gas Separator
The following report is a study of the separating qualities of a loop-type separator that can obtain separation with a smaller pressure drop.
Date:
November 17, 1951
Creator:
Barlow, J. W.; Jones, F. H. & Reuther, R. H.
Object Type:
Report
System:
The UNT Digital Library
Evaluation of a Ducted-Fan Power Plant Designed for High Output and Good Cruise Fuel Economy
Theoretical analysis of performance of a ducted-fan power plant designed both for high-output, high-altitude operation at low supersonic Mach numbers and for good fuel economy at lower fight speeds is presented. Performance of ducted fan is compared with performance (with and without tail-pipe burner) of two hypothetical turbojet engines. At maximum power, the ducted fan has propulsive thrust per unit of frontal area between thrusts obtained by turbojet engines with and without tail-pipe burners. At cruise, the ducted fan obtains lowest thrust specific fuel consumption. For equal maximum thrusts, the ducted fan obtains cruising flight duration and range appreciably greater than turbojet engines.
Date:
October 17, 1950
Creator:
Behun, M.; Rom, F. E. & Hensley, R. V.
Object Type:
Report
System:
The UNT Digital Library
Lift and Drag Characteristics of the Bell X-5 Research Airplane at 59 Degrees Sweepback for Mach Numbers from 0.60 to 1.03
Report presenting an investigation of the flight characteristics of the Bell X-5 research airplane with sweepback that can be varied from 20 degrees to 59 degrees in flight. Lift and drag data have been obtained for the 59 degree sweep configuration for a range of Mach numbers and from zero to almost maximum lift.
Date:
February 17, 1953
Creator:
Bellman, Donald R.
Object Type:
Report
System:
The UNT Digital Library