Resource Type
Serial/Series Title
NACA Research Memorandums
493
NACA Technical Notes
273
Atomic Energy Commission Reports
170
Oak Ridge National Laboratory Reports
152
CF (Series)
138
United States Geological Survey Reports
79
Trace elements investigations report
67
University of California Radiation Laboratory Reports
60
NACA Technical Reports
30
United States Bureau of Mines Reports
23
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1,379 Matching Results
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Report #26: Development of Photomultiplier Tubes
From Large Area Multiplier Phototubes: "Figure 1 illustrates the nature of the design required as compared to the cone design utilized previously, Fig. 2. The metal cone shown in Figure 1 will be welded onto flange of the cone in Figure 2."
Date:
December 1957
Creator:
Schenkel, F. W. & Snell, P. A.
Object Type:
Report
System:
The UNT Digital Library
Synthesis and Properties of Carnotite and its Alkali Analogues
A report which records the results of experiments dealing with the synthesis of carnotite and its alkali analogues. The work was primarily concerned with the preparation of single crystals suitable for detailed structural analysis, though some insight into the chemistry of the precipitation of carnotite was obtained.
Date:
December 1957
Creator:
Barton, Paul B., Jr.
Object Type:
Report
System:
The UNT Digital Library
A Thermocouple Subcarrier Oscillator for Telemetering Temperatures From Pilotless Aircraft
Note presenting a subcarrier oscillator which, in conjuncting with a telemetering system, gives a satisfactory method for telemetering temperatures by means of thermocouples from pilotless aircraft. The method results in an oscillator having a small size, low microphonics, high input resistance, and satisfactory stability if a switch is used to commutate calibration voltages along with the pickups.
Date:
December 1957
Creator:
Fricke, Clifford L.
Object Type:
Report
System:
The UNT Digital Library
Three-Degree-of Freedom Evaluation of the Longitudinal Transfer Functions of a Supersonic Canard Missile Configuration Including Changes in Forward Speed
Note presenting a reevaluation of existing flight data obtained for a supersonic canard missile configuration of the boost-glide type to determine derivatives not previously evaluated. The derivatives are utilized to determine some typical airframe frequency responses based on the three-degree-of-freedom longitudinal equations of motion. Results regarding derivatives, frequency responses, and three-degree-of-freedom approach to future automatic-control studies are provided.
Date:
December 1957
Creator:
Seaberg, Ernest C.
Object Type:
Report
System:
The UNT Digital Library
Transition-flight investigation of a four-engine-transport vertical-take-off airplane model utilizing a large flap and extensible vanes for redirecting the propeller slipstream
Report presenting an experimental investigation to determine the dynamic stability and control characteristics of a four-engine-transport vertical-take-off airplane model in the transition range from hovering to normal forward flight. Both flight and static-force tests were conducted and flight testing was carried out with a pitch damper installed. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date:
December 1957
Creator:
Tosti, Louis P.
Object Type:
Report
System:
The UNT Digital Library
Turbulence measurements in multiple interfering air jets
Report presenting turbulent and mean-flow characteristics of several noise-suppression multiple-jet nozzles from hot-wire-anemometer measurements for the flow conditions at Mach number 0.3. The measurements show that turbulent mixing, as indicated by reduced intensity and scale of turbulence, occurs closer to the nozzle in interfering than in noninterfering jets. Results regarding mean flow, turbulent flow, and scale or eddy size are provided.
Date:
December 1957
Creator:
Laurence, James C. & Benninghoff, Jean M.
Object Type:
Report
System:
The UNT Digital Library
Velocity and friction characteristics of laminar viscous boundary-layer and channel flow over surfaces with ejection or suction
Report presenting some information on flow characteristics - velocity field, pressure drop, and friction - for steady, fully developed laminar flow through a duct consisting of two parallel walls, for flow throguh tubes with circular cross section, and for boundary-layer flow over infinite wedges. In order to determine the extent to which the boundary conditions imposed o the flow by the various geometries influence the flow characteristics, dimensionless parameters common to both channel and boundary-layer flow were developed.
Date:
December 1957
Creator:
Eckert, E. R. G.; Donoughe, Patrick L. & Moore, Betty Jo
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability
Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date:
December 3, 1957
Creator:
Dunning, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Model of an Escape Capsule for a Supersonic Bomber-Type Airplane at a Mach Number of 2.49
Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.
Date:
December 3, 1957
Creator:
Presnell, John G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effects of string-support interference on the drag of an olgive-cylinder body with and without a boatail at 0.6 to 1.4 Mach number
Report presenting tests to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Results regarding the effect of sting length and sting diameter are provided.
Date:
December 3, 1957
Creator:
Lee, George & Summers, James L.
Object Type:
Report
System:
The UNT Digital Library
Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations
"The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tests; one was a 60deg delta wing and the other was a trapezoid wing having an aspect ratio of 3, taper ratio of 0.143, and an unswept 80-percent-chord line" (p. 1).
Date:
December 3, 1957
Creator:
Sleeman, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03
Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Date:
December 5, 1957
Creator:
West, F. E., Jr.; Whitcomb, Charles F. & Schmeer, James W.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Transonic Longitudinal and Lateral Handling Qualities of the Douglas X-3 Research Airplane
Memorandum presenting a flight investigation to determine the longitudinal and lateral handling qualities of the Douglas X-3 research airplane in the clean configuration. Static and dynamic stability and control characteristics were determined during trimmed and maneuvering flight at an average altitude of 30,000 feet and over a Mach number range from 0.7 to 1.16.
Date:
December 5, 1957
Creator:
Fischel, Jack; Holleman, Euclid C. & Tremant, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces Having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift
Memorandum presenting an investigation of the use of low auxiliary horizontal-tail surfaces to alleviate the pitch-up tendency at high lift of an airplane configuration with a T-tail. The basic model had a wing with an aspect ratio of 3, a taper ratio of 0.143, and an unswept 80-percent chord line.
Date:
December 5, 1957
Creator:
Sleeman, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Normal-force and hinge-moment characteristics at transonic speeds of flap-type ailerons at three spanwise locations on a 4-percent-thick sweptback-wing-body model and pressure distribution measurements on an inboard aileron
Report presenting an investigation conducted at the 16-foot transonic tunnel to determine the loading characteristics of flap-type ailerons located at inboard, midspan, and outboard positions on a 45 degree sweptback-wing-body combination. Results indicated that the loading over the ailerons was established by the wing-flow characteristics and the loading shapes were irregular in the transonic speed range.
Date:
December 5, 1957
Creator:
Runckel, Jack F. & Hieser, Gerald
Object Type:
Report
System:
The UNT Digital Library
The effects of boundary-layer separation over bodies of revolution with conical tail flares
The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of pressure, pressure distributions, and lift and drag coefficients were determined for various bodies of revolution with conical tail flares at Mach numbers from 3.0 to 6.3. Some of the experimental results are compared to theoretical predictions of the aerodynamic characteristics of the bodies.
Date:
December 12, 1957
Creator:
Dennis, David H.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of the simulation of atmospheric entry of ballistic missiles
Report presenting a small-scale apparatus for simulating the motion and heating of ballistic missiles and its elements of design and operation. Experiments demonstrate that conditions for simulation are fulfilled according to theoretical requirements. Results regarding the application to full-scale missiles, shadowgraph observations, observations of recovered models, and spectroscopic observations are provided.
Date:
December 12, 1957
Creator:
Neice, Stanford E.; Carson, James A. & Cunningham, Bernard E.
Object Type:
Report
System:
The UNT Digital Library
In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System
Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date:
December 12, 1957
Creator:
Saltzman, Edwin J.
Object Type:
Report
System:
The UNT Digital Library
In-flight gains realized by modifying a twin side-inlet induction system
Report presenting the effects of modifying a twin side-inlet duct system on an interceptor airplane over a range of altitudes throughout the transonic speed range to Mach number 1.2. The primary modifications were redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date:
December 12, 1957
Creator:
Saltzman, Edwin J.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Control Effectiveness of Tip Ailerons and Spoilers on a Low-Aspect-Ratio Trapezoidal-Wing Airplane Model at Mach Numbers From 1.55 to 2.35
Memorandum presenting a wind-tunnel investigation of the three types of lateral control devices on a low-aspect-ratio trapezoidal wing. Tip ailerons, a plain spoiler, and a vented spoiler were investigated to ascertain the relative characteristics of each system. The results indicated the superiority in roll power of the tip ailerons over the plain and vented ailerons.
Date:
December 12, 1957
Creator:
Wong, Norman D.
Object Type:
Report
System:
The UNT Digital Library
Theoretical and Experimental Investigation of Arbitrary Aspect Ratio, Supercavitating Hydrofoils Operating Near the Free Water Surface
Report presents a comparison of the theoretical and experimental expressions of lift, drag, and center of pressure of supercavitating hydrofoils. The results obtained from both methods appear to agree well with one another. The application of cavitation number to a variety of situations and speeds is also provided.
Date:
December 12, 1957
Creator:
Johnson, Virgil E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Delta-Phase Zirconium Hydride as a Solid Moderator
Abstract: "In a study of the preparation and properties of delta-phase zirconium hydride it was found that large, sound bodies of the hydride can be prepared by direct combination of the elements if the rate of the reaction is retarded by limiting the supply of available hydrogen. Specimens up to 1-in. diameter were prepared using this technique. Because delta phase zirconium hydride does not readily form eutectics with iron-and nickel-base alloys below 1800 F these materials may be utilized for clodding the hydride. Delta-phase zirconium hydride is unaffected by exposure to liquid NaK or to nitrogen gas at temperatures below 1000 F. The hot hardness of delta-phase zirconium hydrid is about 130 kg per mm-2 at room temperature and 40 kg per mm-2 at 1500 F. The mean coefficient of thermal expansion (68 to 1337 F) is 6.5 x 10^-6 per deg F. The thermal conductivity varies from 5.7 Btu/(ft)(hr)(F) at 300 F to 5.1 Btu/(ft)(hr)(F) at 1300 F."
Date:
December 18, 1957
Creator:
Vetrano, James B.
Object Type:
Report
System:
The UNT Digital Library
Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power
Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date:
December 19, 1957
Creator:
Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Object Type:
Report
System:
The UNT Digital Library
Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70
"Boundary-layer transition and heat-transfer measurements were obtained from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach number range of 1.25 to 3.75" (p. 1).
Date:
December 19, 1957
Creator:
Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Object Type:
Report
System:
The UNT Digital Library