2,620 Matching Results

Search Results

Advanced search parameters have been applied.

Preliminary Investigation of Effects of Alpha-Particle Bombardment on the Creep Rate of Aluminum

Description: Memorandum presenting a preliminary investigation to determine the effects of alpha-particle bombardment on the creep rate of aluminum wire at 400 degrees Fahrenheit. The alpha radiation from an 85-millicurie polonium source appeared to decrease slightly the creep rate of the aluminum.
Date: July 3, 1947
Creator: Kittel, J. Howard
Partner: UNT Libraries Government Documents Department

Laminar Natural-Convection Flow and Heat Transfer of Fluids With and Without Heat Sources in Channels With Constant Wall Temperatures

Description: Note presenting an analysis of the natural-convection phenomenon, which shows that the flow and heat transfer, in general, are not only functions of the Prandtl and Grashof numbers but also depend on a new dimensionless parameter. If the parameter is not negligibly small, the compression work and frictional heating may appreciably affect this mode of heat transfer. Results regarding the velocity and temperature distributions and heat transfer are provided.
Date: December 1952
Creator: Ostrach, Simon
Partner: UNT Libraries Government Documents Department

NACA Investigation of Fuels Corresponding to Specification an-F-58 : Results of Studies in Single Combustors of J-33, J-34, J-35, and Nene Turbojet Engines

Description: "The NACA is engaged in a program to evaluate the performance of fuels conforming to AN-F-58 specification in both full-scale engines and single combustors. This research memorandum constitutes an interim report on the results obtained on single cosibustors" (p. 1).
Date: November 16, 1945
Creator: Cleveland Laboratory Staff
Partner: UNT Libraries Government Documents Department

Lift-Cancellation Technique in Linearized Supersonic-Wing Theory

Description: Note presenting a lift-cancellation technique for determining load distributions on thin wings at supersonic speeds. A general expression is derived for the load distribution over a cancellation wing. The lift cancellation technique is illustrated for swept wings with curvilinear plan forms.
Date: August 1950
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department

Investigation of Fretting Corrosion by Microscopic Observation

Description: Note presenting an investigation using microscopic observation of the action to determine the cause of fretting corrosion. Glass and other noncorrosive materials, as well as metals, were used as specimens. Results regarding metal against metal, metal against nonmetal, and nonmetals against nonmetals are provided.
Date: February 1950
Creator: Godfrey, Douglas
Partner: UNT Libraries Government Documents Department

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
Partner: UNT Libraries Government Documents Department

Fuel Consumption Corrected for Cooling Drag of an Air-Cooled Radial Aircraft Engine at Low Fuel-Air Ratios and With Variable Spark Advance

Description: Report presenting results of tests conducted with an air-cooled, radial aircraft engine to determine the reduction in the brake specific fuel consumption that would result from operating with a very low fuel-air ratio and an increased spark advance. Computed values of the brake specific fuel consumption corrected for cooling-air drag are also given.
Date: February 1945
Creator: Munger, Maurice
Partner: UNT Libraries Government Documents Department

Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Partner: UNT Libraries Government Documents Department

Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control

Description: Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date: August 16, 1955
Creator: Conrad, E. William
Partner: UNT Libraries Government Documents Department

High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor

Description: Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.
Date: December 9, 1954
Creator: Butze, Helmut F.
Partner: UNT Libraries Government Documents Department

High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels

Description: Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date: April 2, 1957
Creator: Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department

Investigation of Internal Film Cooling of 1000-Pound-Thrust Liquid-Ammonia - Liquid-Oxygen Rocket-Engine Combustion Chamber

Description: Memorandum presenting an investigation of internal film cooling of the combustion chamber of a 1000-pound-thrust liquid-ammonia-liquid-oxygen rocket engine. The three coolants studied were water, ethyl alcohol, and liquid ammonia. Results regarding heat-transfer results, liquid film-cooled length, correlation of heat-transfer data, and effect of film cooling on performance are provided.
Date: July 17, 1951
Creator: Morrell, Gerald
Partner: UNT Libraries Government Documents Department

Investigation of Rotating Components of Counterrotating Two-Spool Engines 1: Analytical Investigation of Off-Design Performance of Turbine Component Designed With and Without Outer-Turbine Stator

Description: Memorandum presenting an investigation to determine the off-design characteristics of a counterrotating turbine component in a two-spool turbojet engine. The results indicated that the inner turbine was conventional with respect to off-design characteristics when considered as a separate unit. Results regarding the performance with and without the outer-turbine stator are provided.
Date: January 10, 1955
Creator: Steward, Warner L.
Partner: UNT Libraries Government Documents Department

Investigation of Transient Pool Boiling Due to Sudden Large Power Surge

Description: Note presenting an investigation of the transfer of heat from a metallic ribbon to water, under transient conditions, for initial water temperatures from 76 to 203 degrees Fahrenheit and average heat-generation rates per square foot of square area of 3, 10, and 20x10(exp 5) Btu per hour per square foot. Results regarding the nucleate boiling region, film boiling region, and critical heat flux are provided.
Date: December 1956
Creator: Cole, Robert
Partner: UNT Libraries Government Documents Department

Interaction of a Free Flame Front With a Turbulence Field

Description: Note presenting the use of small-perturbation spectral-analysis techniques to obtain the root-mean-square flame-generated turbulence velocities and the attenuating pressure fluctuations stemming from interaction of a constant-pressure flame front with a field of isotropic turbulence in the absence of turbulence decay processes.
Date: March 1955
Creator: Tucker, Maurice
Partner: UNT Libraries Government Documents Department

Injection Principles for Liquid Oxygen and Heptane Using Nine-Element Injectors in an 1800-Pound-Thrust Rocket Engine

Description: Memorandum presenting a study of six nine-element injectors for the liquid-oxygen-heptane propellant system in an 1800-pound-thrust rocket engine. The characteristic velocities for comparable injector types were about the same as those obtained from the two-element study. The level of performance was generally higher for the nine-element injectors.
Date: July 18, 1957
Creator: Neu, Richard F.
Partner: UNT Libraries Government Documents Department

Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application

Description: "A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).
Date: November 16, 1953
Creator: Hoffman, Charles A.
Partner: UNT Libraries Government Documents Department

Simple Graphical Solution of Heat Transfer and Evaporation From Surface Heated to Prevent Icing

Description: "Equations expressing the heat transfer and evaporation from wetted surfaces during ice prevention have been simplified and regrouped to permit solutions by simple graphical means. Working charts for quick and accurate anti-icing calculations are also included" (p. 1).
Date: October 1952
Creator: Gray, Vernon H.
Partner: UNT Libraries Government Documents Department

Simplified Method for Estimating Compressible Laminar Heat Transfer With Pressure Gradient

Description: "In the present report an approximation is made in the method of Technical Note 3326, which simplifies the calculation of heat transfer. Good agreement with the method of Technical Note 3326 is expected for isothermal surfaces with adverse and small favorable pressure gradients regardless of surface temperature and also for flow with large favorable pressure gradient over highly cooled surfaces" (p. 1).
Date: December 1956
Creator: Reshotko, Eli
Partner: UNT Libraries Government Documents Department

Skin Friction of Incompressible Turbulent Boundary Layer Under Adverse Pressure Gradients

Description: Note presenting experimental data for skin friction of turbulent boundary layers under adverse pressure gradients from several sources in graphical form. Data obtained by the momentum-balance method are shown to follow a trend opposite to that of data obtained by hot-wire and heat-transfer methods.
Date: August 1951
Creator: Goldschmied, Fabio R.
Partner: UNT Libraries Government Documents Department

Some Linear Dynamics of Two-Spool Turbojet Engines

Description: Note presenting general equations for the linear responses of inner- and outer-spool speed to change in turbine-inlet temperature and exhaust-nozzle area are derived and evaluated from hypothetical two-spool-engine characteristics at design speed. Experimental corroboration of analysis is also provided in the form of response to fuel flow, response to exhaust-nozzle area, and response to turbine-inlet temperature are provided.
Date: June 1956
Creator: Novik, David
Partner: UNT Libraries Government Documents Department

Turning-Angle Design Rules for Constant-Thickness Circular-Arc Inlet Guide Vanes in Axial Annular Flow

Description: Note presenting a survey of data from investigations of axial-flow-compressor inlet guide vanes with circular-arc, constant-thickness sections and axial air inlet to establish a relation between vane camber and air turning angle for use in the design of this type of vane. Results regarding design rules for convergent annuli, example of the straight-line rule, design rule for constant axial velocity, and the comparison and use of design rules are provided.
Date: September 1950
Creator: Lieblein, Seymour
Partner: UNT Libraries Government Documents Department

Theoretical Investigation of Velocity Diagrams of a Single-Stage Turbine for a Turbojet Engine at Maximum Thrust Per Square Foot Turbine Frontal Area

Description: Note presenting an exploratory velocity-diagram analysis made in order to establish the aerodynamic requirements of a single-stage, axial-flow turbine which satisfies the conditions of maximum thrust per square foot of turbine frontal area in a turbojet engine. The investigation was made over a range of turbine mean blade speeds and inlet temperatures, fixed flight conditions, and a constant centrifugal stress at the root of the rotor blading. A comparison was made employing conventional turbine aerodynamic design limits for one set of conditions from the analysis.
Date: June 1952
Creator: Cohen, Leo
Partner: UNT Libraries Government Documents Department