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

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Experimental investigation of the simulation of atmospheric entry of ballistic missiles

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Transonic Longitudinal and Lateral Handling Qualities of the Douglas X-3 Research Airplane

Description: 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.
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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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

Description: "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 … more
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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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
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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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In-flight gains realized by modifying a twin side-inlet induction system

Description: 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.
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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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

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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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Isolation and Identification of an Ester from a Crude Oil

Description: Abstract: "A dioctylphthalate has been isolated from a crude oil by means of adsorption column chromatography. The ester was identified by means of elemental analysis, refractive index, and its infrared adsorption spectrum. Saponification of the isolate and examination of the resultant alcohol by means of infrared adsorption spectra led to the conclusion that the ester is a branched chain dioctylphthalate. This is the first reported occurrence of an ester in crude petroleum."
Date: December 1957
Creator: Phillips, Harry F. & Breger, Irving A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A laboratory Ivestigation of the Fluorination of Crude Uranium Tertrafluoride

Description: Ore concentrates have been converted directly to crude uranium tetrafluoride by hydrogen reduction and hydrofluorination in fluidized-bed reactors. Small-scale laboratory experiments demonstrated that this process can be extended to the production of crude uranium hexafluoride through fluorination of the uranium tetrafluoride in a fluidized bed. The satisfactory temperature range for the reaction lies between 300°C and 600°C. At 450°C the fluorine utilization is between 50 and 80 per cent. With… more
Date: December 1957
Creator: Sandus, O. & Steunenberg, R. K.
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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Liquid Metal Fuel Reactor Experiment (Phase 1C): Supplement to LMFRE Reference Design Report

Description: This supplement describes a number of modifications to the Liquid Metal Fuel Reactor Experiment (LMFRE), including (1) engineering design changes to achieve economies in the original reference design, and (2) a revised cost estimate that reapportions the various construction, research and development, and operating costs in accordance with procedures established by the Atomic Energy Commission.
Date: December 1957
Creator: Babcock & Wilcox Company
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Report of the Forty-Second National Conference on Weights and Measures, 1957

Description: Report of the annual conference on weights and measures, hosted by the U.S. National Bureau of Standards in Washington D.C. It includes conference proceedings, a list of attendees, information about committees and officers, and other reports or commentaries discussed at the meetings.
Date: December 20, 1957
Creator: United States. National Bureau of Standards.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Description: 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
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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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
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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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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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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: TED No. NACA AD 3116

Description: Memorandum 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 with external wing fuel tanks installed. The results indicated that any fully developed erect spin obtained on the airplane with tanks installed will be satisfactorily terminated by rudder reversal accompanied by moving the ailerons to full with the spin.
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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Synthesis and Properties of Carnotite and its Alkali Analogues

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