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Determination of vortex paths by series expansion technique with application to cruciform wings

Description: A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory ag… more
Date: February 8, 1956
Creator: Alksne, Alberta Y.
open access

Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with area suction boundary-layer control on the flaps

Description: Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics o… more
Date: February 3, 1956
Creator: Anderson, Seth B. & Quigley, Hervey C.
open access

Development test 105-623A: Relation between hand and flow seating of slug charges as they affect slug rupture rates

Description: A large portion of the slug failures which occurred during 1955 were of the ``hot-spot`` type. Observation of these failures has shown them to be the result of intergranular corrosion attack of the aluminum jacket. Intergranular corrosion is presently considered to occur in water temperature above 150 C; a flow disturbance which causes non-uniform coolant temperatures is suspected as the cause of failure.The present of a cocked slug, or a bowed slug column, might provide this flow disturbance. … more
Date: February 13, 1956
Creator: Arneson, S. O. & VanWormer, F. W.
open access

Effects of Rocket-Armament Exhaust Gas on the Performance of a Supersonic-Inlet J34-Turbojet-Engine Installation at Mach 2.0

Description: Report presenting an investigation of the effects of rocket-armament-exhaust-gas ingestion on the performance of a supersonic-inlet J34-turbojet-engine installation at Mach 2. Rockets were fired from two different spike positions and with the engine at high or low speed. Results regarding engine air flow, temperature, and flame-out are provided.
Date: February 20, 1956
Creator: Beheim, Milton A. & Evans, Phillip J.
open access

TEMPERATURE DISTRIBUTION AND THERMAL STRESS IN REACTOR CORE APPR-1

Description: The feasibility of the Liquid Metal Fuel Reactor (LMFR) proposed by Brookhaven National Laboratory as a source of electric power was thoroughly investigated. The reference design is based on an LMFR using U dissolved in Bi as the fuel and a thorium bismuthide in Bi slurry as the blanket. Detailed estimates of power costs are presented for electrical power stations from 226 to 904 Mw net electrical capability. (C.W.H.)
Date: February 15, 1956
Creator: Berggren, W. P. & Kroeger, H. R.
open access

Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9

Description: Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.
Date: February 9, 1956
Creator: Bertram, Mitchel H.
open access

An investigation of the aerodynamic characteristics at transonic Mach numbers of a swept-wing supersonic bomber configuration

Description: Report presenting an investigation of the aerodynamic characteristics of a swept-wing supersonic bomber configuration conducted in the 8-foot transonic tunnel. The wing had an aspect ratio of 3.5, taper ratio of 0.2, 47 degrees of sweepback of the 0.25-chord line, and airfoil sections which were 5.5 percent thick parallel to the plane of symmetry. Results regarding the longitudinal force characteristics, effects of wing incidence, a modified wing, various auxiliary wing devices, and horizontal-… more
Date: February 1, 1956
Creator: Bielat, Ralph P. & Cooper, J. Lawrence
open access

Low-speed longitudinal stability and lateral-control characteristics of a model of a 40 degree swept-wing fighter-type airplane at a Reynolds number of 9 x 10(exp 6)

Description: Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.
Date: February 3, 1956
Creator: Bollech, Thomas V. & Kelly, H. Neale
open access

Effect of pneumatic de-icers and ice formations on aerodynamic characteristics of a airfoil

Description: Report presenting measurements of lift, drag, and pitching moment of an NACA 0011 airfoil in icing using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes. Results regarding the airfoil characteristics with the de-icer operating and effect of primary ice formation on drag, lift, and pitch with the de-icer inoperative are provided.
Date: February 1956
Creator: Bowden, Dean T.
open access

Transonic Wind-Tunnel Investigation of the Aerodynamic Loading Characteristics of a Highly Tapered Upswept Wing in the Presence of a Body With and Without Indentation

Description: Memorandum presenting a transonic investigation of the aerodynamic loading characteristics and the effects of body indentation on the wing loads of a low-aspect-ratio, highly tapered, unswept wing in the presence of a body in the 8-foot transonic pressure tunnel. The tests covered a range of Mach numbers from 0.60 to 1.20 for angles of attack from 0 to 20 degrees. Results regarding the basic aerodynamic characteristics, basic center-of-pressure characteristics, effect of body indentation, divis… more
Date: February 1956
Creator: Brooks, Joseph D.
open access

Tabulated Pressure Coefficient Data from a Tail Loads Investigation on a 1/15-Scale Model of the Goodyear XZP5K Airship

Description: This paper contains tail and hull loads data obtained in an investigation of a l/15-scale model of the Goodyear XZP5K airship. Data are presented in the form of tabulated pressure coefficients over a pitch and yaw range of +/-20 deg and 0 deg to 30 deg respectively, with various rudder and elevator deflections. Two tail configurations of different plan forms were tested on the model. The investigation was conducted in the Langley full-scale tunnel at a Reynolds number of approximately 16.5 x 10… more
Date: February 15, 1956
Creator: Cannon, Michael D.
open access

The Brazing of Aluminum Bronze to Inconel

Description: The requirements of an atmosphere for the brazing of Al bronze to Inconel were considered on a thermodynamic basis. It was demonstrated that brazing was not possible in a vacuum or inert gas and is improbable in dry H/sub 2/. Attempts to braze in dry H/sub 2/ prove unsuccessful as predicted, except at isolated spots where filler metal had been preplaced. Modification of the plastic binder for holding the filler metal so as to remove Oi and introduce halogen gave no improvement. Negative results… more
Date: February 13, 1956
Creator: Caplan, D.; McCarthy, J. J. & Nippes, E. F.
open access

The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5 - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number, 2.01

Description: Memorandum presenting a supersonic wind-tunnel investigation of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with a large external store.
Date: February 13, 1956
Creator: Carlson, Harry W. & Geier, Douglas J.
open access

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5: Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number 2.01

Description: Report presenting an investigation of store interference in the supersonic pressure tunnel at Mach number 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The interference effects measured at that Mach number were similar to those reported previously at Mach number 1.61. Results regarding store drag, store lift, store side force, store pitching moment and yawing moment, wing-fuselage drag, wing-fuselage lift, total drag, total lift, and wing-fuselage… more
Date: February 13, 1956
Creator: Carson, Harry W. & Geier, Douglas J.
open access

Example of an Antiproton-Nucleon Annihilation

Description: The existence of antiprotons has recently been demonstrated at the Berkeley Bevatron by a counter experiment. The antiprotons were found among the momentum-analyzed (1190 Mev/c) negative particles emitted by a copper target bombarded by 6.2-Bev protons. Concurrently with the counter experiment, stacks of nuclear emulsions were exposed in the beam adjusted to 1090 Mev/c negative particles in an experiment designed to observe the properties of antiprotons when coming to rest. This required a 132 … more
Date: February 27, 1956
Creator: Chamberlain, O.; Chupp, W. W.; Ekspong, A. G.; Goldhaber, G.; Goldhaber, S.; Lofgren, E. J. et al.
open access

Antiproton Interaction Cross Sections

Description: Using the 1.19-Bev/c antiproton beam recently discovered at the Berkeley Bevatron of the University of California, we have measured the attenuation cross section in beryllium and copper. These cross sections are compared to attenuation measurements made with the same geometry using positive protons of the same incident energy (497 MeV).
Date: February 27, 1956
Creator: Chamberlain, Owen; Keller, Donald V.; Segre, Emilio; Steiner,Herbert M.; Wiegand, Clyde & Ypsilantis, Tom
open access

Aerodynamic heating of aircraft components

Description: From Introduction: "The purpose of this paper is to review new and significant data which will be of interest to designers in determining the heating of these components. A comparison with existing theory to indicate its adequacy in each case is also presented."
Date: February 14, 1956
Creator: Chauvin, Leo T.
open access

Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Description: Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date: February 1, 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
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