Technical Report Archive & Image Library (TRAIL) - 60 Matching Results

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Report #26: Development of Photomultiplier Tubes

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Droplet Impingement on Four Bodies of Revolution

Description: An experiment was conducted to obtain the rate and area of cloud droplet impingement on four bodies of revolution was conducted in the icing tunnel with a dye-tracer technique. The study included several forebody shapes of different fineness ratios over a range of angles of attack and rotational speeds. Results regarding velocity distribution, local impingement characteristics, and correlation of impingement characteristics are provided.
Date: December 1957
Creator: Lewis, James P. & Ruggeri, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas F4D-1 Airplane With External Wing Fuel Tanks

Description: Report presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane equipped with external fuel tanks. Results regarding erect spins, inverted spins, and parachute results are provided.
Date: December 27, 1957
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions

Description: "For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."
Date: December 27, 1957
Creator: Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2

Description: Memorandum presenting an investigation of flow surrounding afterbodies behind blunt nose shapes at a Mach number of 2 in the 27- by 27-inch preflight jet. Pressure measurements were made on and around the afterbodies for each configuration.
Date: December 27, 1957
Creator: Speegle, Katherine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations

Description: "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 tes… more
Date: December 3, 1957
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Laminar Boundary Layer With Heat Transfer on a Cone at Angle of Attack in a Supersonic Stream

Description: Note presenting the equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry of a yawed cone. Solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack.
Date: December 1957
Creator: Reshotko, Eli
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat transfer and recovery temperatures on a sphere with laminar, transitional, and turbulent boundary layers at Mach numbers of 2.00 and 4.15

Description: Report presenting an investigation of the pressure and equilibrium-temperature distributions on a sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic heat transfer was measured on a sphere at Mach number 2.00 and on a hemisphere-cylinder at Mach number 4.15. Results regarding pressure distributions, equilibrium and recovery temperatures, heat-transfer coefficients, and effect of roughness on transition are provided.
Date: December 1957
Creator: Beckwith, Ivan E. & Gallagher, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Velocity and friction characteristics of laminar viscous boundary-layer and channel flow over surfaces with ejection or suction

Description: 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 b… more
Date: December 1957
Creator: Eckert, E. R. G.; Donoughe, Patrick L. & Moore, Betty Jo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Thermocouple Subcarrier Oscillator for Telemetering Temperatures From Pilotless Aircraft

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the effects of propeller diameter on the ability of a flapped wing, with and without boundary-layer control, to deflect a propeller slipstream downward for vertical take-off

Description: Report presenting an investigation to study the effects of propeller diameter on the ability of a flapped wing, with and without boundary-layer control, to deflect propeller slipstreams downward for vertical take-off. The results indicated that without boundary-layer control, an increase in the ratio of flap chord to propeller diameter increases the turning angle but decreases the ratio of resultant force to thrust.
Date: December 1957
Creator: Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Description: From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."
Date: December 1957
Creator: Aiken, William S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Three-Degree-of Freedom Evaluation of the Longitudinal Transfer Functions of a Supersonic Canard Missile Configuration Including Changes in Forward Speed

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A reexamination of the use of simple concepts for predicting the shape and location of detached shock waves

Description: A reexamination has been made of the use of simple concepts for predicting the shape and location of detached shock waves. The results show that simple concepts and modifications of existing methods can yield good predictions for many nose shapes and for a wide range of Mach numbers.
Date: December 1957
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge blunting on the local heat transfer and pressure distributions over flat plates in supersonic flow

Description: Report presenting an investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting at Mach number 4 and free-stream Reynolds numbers per inch of 2380 and 6600. For test conditions, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. Results regarding surface pressure, flow-field surveys, heat transfer, boundary-layer thickness, surface pressure distribution, local… more
Date: December 1957
Creator: Creager, Marcus O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of overheating on creep-rupture properties of S-816 alloy at 1,500 degrees F

Description: The effects of overheats to temperatures of 1650, 1800, 1900, and 2000 F were evaluated in terms of the changes in creep-rupture characteristics at 1500 F of S-816 alloy under stresses within the range of rupture strengths of the alloy for 100 to 1000 hours. Overheat periods were predominantly of 2-minute duration and were applied cyclically at approximately 5- or 12-hour intervals. The possible damage from overheating was believed to include internal metal structure changes induced by exposure… more
Date: December 1957
Creator: Rowe, John P. & Freeman, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Abnormal grain growth in nickel-base heat-resistant alloys

Description: From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."
Date: December 1957
Creator: Decker, R. F.; Rush, A. I.; Dano, A. G. & Freeman, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of overheating on creep-rupture properties of HS-31 alloy at 1,500 degrees F

Description: Report presenting an investigation of overheating HS-31 alloy to four different temperatures during the course of rupture tests at 1500 degrees Fahrenheit. The intent was to develop basic information on the effect of overheats on creep-rupture properties so as to assist in the evaluation of damage from overheating during gas-turbine operation. Results regarding the rupture properties of test material, overheating in the absence of stress, overheating in the presence of stress, microstructural e… more
Date: December 1957
Creator: Rowe, John P. & Freeman, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbulence measurements in multiple interfering air jets

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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