Technical Report Archive & Image Library (TRAIL) - 160 Matching Results

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Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane

Description: "An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).
Date: July 13, 1955
Creator: Windham, John O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of blunt-trailing-edge elevons on the longitudinal and lateral handling qualities of the semitailless airplane

Description: Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.
Date: January 13, 1955
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids

Description: Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.
Date: May 13, 1954
Creator: Caves, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Factors Affecting Lateral Stability and Controllability

Description: The effects on dynamic lateral stability and controllability of some of the important aerodynamic and mass characteristics are discussed and methods are presented for estimating the various stability parameters to be used in the calculation of the dynamic lateral stability of airplanes with swept and low-aspect-ratio wings.
Date: May 13, 1948
Creator: Campbell, John P. & Toll, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities From Flights of P-61C Airplanes Within Thunderstorms July 31, 1947 to August 6, 1947 at Clinton County Army Air Field, Ohio

Description: Memorandum presenting the results of measurements of gust and draft velocities within thunderstorms at an air field over a 7-day period. The data are summarized in tables and compared to previous flights.
Date: February 13, 1948
Creator: Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers

Description: Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date: April 13, 1950
Creator: Gabriel, David S.; Dowman, Harry W. & Jones, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of flow fluctuations during surge and blade row stall in axial-flow compressors

Description: "A preliminary investigation of the flow fluctuations of surge and blade row stall was conducted with three single-stage axial-flow compressors with hub-tip ratios of 0.9,0.8, and 0.5 and with a multistage axial-flow compressor. Flow fluctuations of large amplitude associated with stall were detected in all compressors investigated. The fluctuations were caused by low flow regions affecting 25 to 40 percent of the annulus area and propagating in the direction of compressor rotation, but at a lo… more
Date: August 13, 1952
Creator: Huppert, Merle C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contribu… more
Date: August 13, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the… more
Date: August 13, 1952
Creator: Abramovitz, Marvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Description: Report presenting an experimental investigation to determine the thrust augmentation possible by the injection of liquid ammonia into the compressor inlet of an axial-flow-type turbojet engine. Results regarding the selection of coolant, cooling with liquid ammonia, engine performance, and operating experience are provided.
Date: August 13, 1952
Creator: Harp, James L., Jr.; Useller, James W. & Auble, Carmon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor

Description: Report presenting an investigation to determine the importance of molecular-scale processes in the overall turbojet combustion process. The effect of oxygen concentration on the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 combustor was determined for a range of combustor-inlet pressures and a range of fuel-flow rates. At a given fuel-flow rate, combustion efficiency decreased at an increasing rate with reduction in oxygen concentration.
Date: August 13, 1952
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Relation of Wind Shear and Insolation to the Turbulence Encountered by an Airplane in Clear-Air Flight at Low Altitudes

Description: Memorandum presenting the observed gust experience of an airplane and information on the associated meteorological conditions to obtain a simple empirical relation for estimating the intensity of turbulence in the earth's friction layer. The relation does not discriminate between differences in turbulence intensity resulting from variations of flight altitude or diurnal variations of turbulence.
Date: September 13, 1951
Creator: Thompson, James K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: The results of an altitude test-chamber investigation of the effects of a number of design changes and operating conditions on altitude peformance of a 28-inch diameter ram jet engine are presented. Most of the investigation was for a simulated flight Mach number of 2.0 above the tropopause. Fuel-air distribution, gutter width, the presence of a pilot flame, cimbustion-chamber-inlet temperature, and exhaust-nozzle throat area were found to have significant effects on limits of combustion. Combu… more
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Magnitude of Vibratory Load Superimposed on Mean Tensile Load on Mechanism of and Time to Fracture of Specimens and Correlation to Engine Blade

Description: Memorandum presenting tensile fatigue tests run on seven turbine-blade alloys at a temperature of 1500 degrees Fahrenheit and a mean stress of 22,000 pounds per square inch with superimposed alternating stresses of 0, 5000, 10,000, and 15,000 pounds per square inch. The same three types of fracture occurring in turbine blades - stress-rupture, stress-rupture followed by fatigue, and fatigue - were obtained in the specimens. Results regarding the effect of alternating stress on mechanism of fail… more
Date: November 13, 1952
Creator: Ferguson, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Internal performance of several types of jet-exit configurations for supersonic turbojet aircraft

Description: Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraf… more
Date: January 13, 1953
Creator: Fleming, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of radiant energy on vaporization and combustion of liquid fuels

Description: Report presenting an investigation of the radiative processes involved in combustion to determine the present role of radiant energy transfer in combustors. The equivalent gray-body emissivity of a hydrocarbon fuel may be increased by use of liquid or solid, soluble or nonsoluble, additives. Results regarding the experimental apparatus and methods, emission characteristics of luminous and nonluminous flames, absorptivity of fuels and of solutions of possible additives, and absorption by slurrie… more
Date: November 13, 1952
Creator: Berlad, A. L. & Hibbard, R. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85

Description: Report presenting an experimental investigation conducted a Mach number of 3.85 to determine the diffuser characteristics of a series of conventional axially symmetric nose inlets on a ramjet in a supersonic wind tunnel. Performance evaluations of single-cone, double-cone, and isentropic diffusers were made in terms of total pressure recovery and mass flow for a range of angles of attack. Results regarding performance of 1-cone inlets, performance of 2-cone inlets, and performance of isentropic… more
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85

Description: Report presenting an experimental investigation at a Mach number of 3.85 in the supersonic wind tunnel to study the flow patterns at the throat of a two-dimensional single-shock diffuser and to evaluate qualitatively several schemes for improving the turning conditions. Schileren observations were made for supercritical inlet operation and conditions of maximum total-pressure recovery.
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Longitudinal Control Characteristics of a Wing-Tip Control Surface on a Sweptback Wing at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation of the longitudinal control effectiveness of a full-chord wing-tip control surface on a wing with 35 degrees of sweepback, 12 percent thickness perpendicular to the quarter-chord line, an aspect ratio of 3.01, and a taper ratio of 0.605 at a range of Mach numbers. Wing-tip control was only 1/6 as effect in producing pitching moment at subsonic speeds as a flap type control and 1/2 as effect at low-supersonic speeds.
Date: June 13, 1952
Creator: Trant, James P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Transfer of Heat From a Flat Plate at a Mach Number of 1.5

Description: "Surface temperatures and heat transfer to the air stream have been measured for turbulent flow over a flat plate at a Mach number of 1.5 and at a Reynolds number, based on the momentum thickness of the boundary layer, of approximately 5000. Preliminary data are presented and the surface heat-transfer coefficients calculated from these data are considered to be accurate to plus or minus 2.6 percent at a temperature potential of 50 degrees Fahrenheit. These data are in good agreement with the re… more
Date: December 13, 1951
Creator: Emmons, M. A., Jr. & Blanchard, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wire cloth as porous material for transpiration-cooled walls

Description: The permeability characteristics and tensile strength of a porous material developed from stainless-steel corduroy wire cloth for use in transpiration-cooled walls where the primary stresses are in one direction were investigated. The results of this investigation are presented and compared with similar results obtained with porous sintered metal compacts. A much wider range of permeabilities is obtainable with the wire cloth than with the porous metal compacts considered and the ultimate tensi… more
Date: November 13, 1951
Creator: Eckert, E. R. G.; Kinsler, Martin R. & Cochran, Reeves P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Characteristics of a 45 Degree Swept Wing with Leading-Edge Inlets

Description: Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 45 degree swept wing with leading-edge inlets. The wing had a constant chord and completely spanned the wind tunnel. Results regarding surface-pressure characteristics, lift and pitching-moment characteristics, wake-drag characteristics, and internal-flow characteristics are provided.
Date: August 13, 1951
Creator: Dannenberg, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Section Thickness and Trailing-Edge Radius on the Performance of NACA 65-Series Compressor Blades in Cascade at Low Speeds

Description: Report presenting tests of NACA 65-series compressor blades cambered to an isolated airfoil lift coefficient of 1.2 at several maximum section thicknesses to obtain the effect of maximum section thickness on section operating characteristics. Information about surface pressure trends, design angle-of-attack selection, drag, operating range, and critical Mach number is also provided. Changing the section thickness was not found to significantly affect the design angle of attack selected.
Date: December 13, 1951
Creator: Herrig, L. Joseph; Emery, James C. & Erwin, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 1: body of revolution with near-parabolic forebody and cylindrical afterbody

Description: An experimental investigation of the aerodynamic characteristics of a slender, square-based body of revolution was conducted at a Mach number of 3.12 for angles of attack from 0 degree to 10 degrees and for Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6). Boundary-layer measurements at zero angle of attack are compared with several compressible flow formulating for predicting boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showe… more
Date: November 13, 1951
Creator: Jack, John R. & Burgess, Warren C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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