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Tests of 16 related airfoils at high speed

Description: From Summary: "In order to provide information that might lead to the development of better propeller section, 13 related symmetrical airfoils were tested in the NACA high-speed wind tunnel for a study of the effect of thickness form on the aerodynamic characteristics. The thickness-form variables studies were the value of the maximum thickness, the position along the chord at which the maximum thickness occurs, and the value of the leading-edge radius. The tests were conducted through the low … more
Date: April 28, 1934
Creator: Stack, John & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over a rectangular airfoil with a partial-span split flap

Description: This report presents the results of pressure-distribution tests of a Clark y wing model with a partial-span split flap made to determine the distribution of air loads over both the wing and the flap. The model was used in conjunction with a reflection plane in the NACA 7 by 10 foot wind tunnel. The 20-percent-chord split flap extended over the inboard 60 percent of the semispan. The tests were made at various flap deflections up to 45 degrees and covered a range of angles of attack from zero li… more
Date: April 28, 1937
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department
open access

Viscosities and Densities of Fluorolube Oils

Description: Abstract: Since the viscosity-temperature relationships of fluorocarbons are somewhat unusual, when compared to hydrocarbons, for example, it was decided to measure the viscosities, at several temperatures, of various fluorolube oils. The calculation of the viscosity of a blend of oils is at best an uncertain operation, varying considerably with the method used. A comparison of various methods was indicated, in order that reasonably accurate values might be assumed for theoretical composites.… more
Date: April 28, 1943
Creator: Haendler, H. M.; Burger, L. L.; Sheldon, Z. D. & Barber, E. J.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85

Description: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date: April 28, 1947
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnels to develop optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Each was equipped with the same flaps and measured at the same Reynolds numbers. Results regarding the lift characteristics and pitching moment are provided.
Date: April 28, 1947
Creator: Cahill, Jones F. & Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department
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The Critical Mass of a Spherical Reactor with Variable Intrinsic Buckling

Description: Abstract: "The critical mass both of an untamped and water-tamped sphere with parabolic radial variation of the intrinsic buckling is calculated by a perturbation method. The result is applied to finding the minimum critical mass of plutonium in water suspension with infinite water temper; the calculations show that the minimum critical mass at constant concentration may be reduced by an amount of the order of 7.6% when the concentration of plutonium is permitted to vary throughout the suspensi… more
Date: April 28, 1949
Creator: Muller, G. M.
Partner: UNT Libraries Government Documents Department
open access

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high al… more
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
open access

Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Similar to One Proposed by Douglas Aircraft Company, Inc.

Description: "At the request of the Air Materiel Command, an investigation was made in the Langley free-flight tunnel to determine the longitudinal stability and control characteristics of models coupled together in a tandem configuration for aerial refueling similar to one proposed by the Douglas Aircraft Company, Inc. Static force tests were made with 1/20-scale models of the B-29 and F-80 airplanes to determine the effects of rigidly coupling the airplanes together. The Douglas configuration differs from… more
Date: April 28, 1950
Creator: Hewes, Donald E.
Partner: UNT Libraries Government Documents Department
open access

Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of the Combustion Properties of a Hydrocarbon Fuel and Several Magnesium and Boron Slurries

Description: Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.
Date: April 28, 1952
Creator: Lord, Albert M.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 1: Aerodynamic Design

Description: Memorandum presenting a 10-stage axial-flow compressor designed for use as a research unit in which the problems associated with the compounding of high performance stages could be studied. The overall performance characteristics of the compressor, as determined experimentally, are included.
Date: April 28, 1952
Creator: Johnsen, Irving A.
Partner: UNT Libraries Government Documents Department
open access

Low-speed aerodynamic characteristics of a large-scale 45 degree swept-back wing with partial-span slats, double-slotted flaps, and ailerons

Description: Report presenting experimental data from force and pressure tests on a large-scale, semispan, wing-fuselage model. Longitudinal force and moment characteristics are given for the model with various combinations of slat spans. The wing had 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and an NACA 64A010 section normal to the quarter-chord line of the unswept panel and had partial-span slats, aileron, and double-slotted flaps equipped.
Date: April 28, 1952
Creator: James, Harry A.
Partner: UNT Libraries Government Documents Department
open access

Performance of an impulse-type supersonic compressor with stators

Description: Report presenting testing of an impulse-type supersonic compressor rotor with stators tested in Freon-12 over a range of equivalent tip speeds and weight flows. A static pressure ratio of 1.83 and an efficiency of 84.7 percent were obtained at 69.1 percent of the design speed of 1604 feet per second in air.
Date: April 28, 1952
Creator: Klapproth, John F.; Ullman, Guy N. & Tysl, Edward R.
Partner: UNT Libraries Government Documents Department
open access

Temperature distribution in the concrete shield

Description: Report describing the temperature in the Brookhaven concrete shield proposed for the X reactor. The report details the methods and equations used to find the values that determined that the effect of the gun barrel assembly in cooling the concrete is negligible.
Date: April 28, 1952
Creator: Triplett, John R.
Partner: UNT Libraries Government Documents Department
open access

Accuracy of Relaxation Length Measurements

Description: We consider here the accuracy of relaxation lengths measured during the water-uranium lattice experiments. Since such an analysis for all measurements would take a great deal of time, we have applied it to just one lattice. This one (2:1 water-to-metal ratio) was chosen completely at random.
Date: April 28, 1953
Creator: Kouts, H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 4: Individual Stage Performance Characteristics

Description: Report presenting a determination of the individual stage performance for a 10-stage axial-flow compressor from circumferentially fixed radial rake measurements of total temperature and total pressure obtained at the discharge of each stage. Results regarding compressor performance, stage performance, and some general remarks are provided.
Date: April 28, 1953
Creator: Budinger, Ray E. & Serovy, George K.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effects of Wing and Tail Modifications on the Low-Speed Stability Characteristics of a Model Having a Thin 40 Degree Swept Wing of Aspect Ratio 3.5

Description: Report presenting an investigation of the effects of wing and tail modifications on the low-speed stability characteristics of a model with thin 40 degree swept wings of aspect ratio 3.5. The main purpose was to improve some of the undesirable longitudinal stability characteristics observed in flight of several airplanes with similar wing geometry. The use of flaps, the position of the horizontal tail, and the use of chord extensions are all explored as possible solutions.
Date: April 28, 1953
Creator: Weil, Joseph; Sleeman, William C., Jr. & Byrnes, Andrew L., Jr.
Partner: UNT Libraries Government Documents Department
open access

Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine

Description: Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficienci… more
Date: April 28, 1953
Creator: Rebeske, John J., Jr. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Studies on Cell Division, 1. Alpha Radiation as a Division Inhibiting Agent

Description: Report discussing a study aimed at learning about cell division and the effects of radiation alpha radiation on the process of cell division. This was done by correlating changes in the biochemical state of cells and the inhibition of cell division. Materials and methods are included as well as experimental results and data.
Date: April 28, 1953
Creator: Spoerl, Edward S. & Balske, R. J.
Partner: UNT Libraries Government Documents Department
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A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

Description: From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."
Date: April 28, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of the Trim and Dynamic Response Characteristics of the Horizontal Tail of a 1/7-Scale Model of the Complete Tail of the Grumman XF10F-1 Airplane

Description: "An investigation was made of the trim and dynamic response characteristics of the free-floating horizontal tail of a 1/7-scale model of the complete tail of the Grumman XF10F-1 airplane in the Langley 8-foot transonic tunnel at Mach numbers up to 1.13. The complete tail was mounted in the tunnel on a 3 degree conical support body. Various configurations were investigated. A loss in damping of the horizontal tail at transonic speeds was shown by both tunnel and flight tests" (p. 1).
Date: April 28, 1953
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
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