5,165 Matching Results

Search Results

Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Description: Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Partner: UNT Libraries Government Documents Department

Preliminary Survey of the Aircraft Fire Problem

Description: Memorandum presenting a review of information relating to aircraft fires to determine what new or further research might lead to a substantial reduction of the aircraft fire hazard in flight and following crashes. An examination of fuels, lubricants, and hydraulic fluids as inflammable liquids is presented, together with possible sources of ignition under the general categories of hot surfaces, electric sparks and arcs, flames, and hot gases.
Date: May 21, 1948
Creator: Cleveland Laboratory Aircraft Fire Research Panel
Partner: UNT Libraries Government Documents Department

Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Date: June 18, 1951
Creator: Selna, James
Partner: UNT Libraries Government Documents Department

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

Problem of Slip Flow in Aerodynamics

Description: Memorandum presenting a survey of the present status of theory in the field of slip-flow aerodynamics, which leads to the conclusion that the Navier-Stokes equations of motion together with first-order velocity slip and temperature jump at any boundary are sufficient insofar as experimental confirmation is available.
Date: March 4, 1957
Creator: Street, Robert E.
Partner: UNT Libraries Government Documents Department

Preliminary Free-Flight Study of the Drag and Stability of a Series of Short-Span Missiles at Mach Numbers From 0.9 to 1.3

Description: Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.
Date: February 8, 1956
Creator: Hall, James Rudyard
Partner: UNT Libraries Government Documents Department

Preliminary Indications of the Cooling Achieved by Ejecting Water Upstream From the Stagnation Point of Hemispherical, 80 Degree Conical, and Flat-Faced Nose Shapes at a Stagnation Temperature of 4,000 F

Description: Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.
Date: October 23, 1957
Creator: Rashis, Bernard
Partner: UNT Libraries Government Documents Department

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions

Description: Memorandum presenting an investigation of the phenomenon of the starting of aerodynamic instability or buzz in supersonic inlets with external compression. The starting of the buzz has been related to the existence in the flow field of a velocity discontinuity across a vortex sheet which originates at a shock intersection. Results regarding the inlets without separation on the central body, inlets with separation on the central body, the regulation of entering volume flow at angles of attack, experimental performance of various inlets, and an application of the results are provided.
Date: January 26, 1951
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Optimum Lifting Bodies at High Supersonic Airspeeds

Description: Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.
Date: May 7, 1954
Creator: Rosnikoff, Meyer M.
Partner: UNT Libraries Government Documents Department

Performance of Separation Nose Inlets at Mach Number 5.5

Description: Memorandum presenting two nose inlets utilizing the boundary-layer separation ahead of a blunt body to provide a compression surface at Mach number 5.5. Results regarding the spherical-nose inlet, the planar-nose inlet, some operating characteristics, and a comparison with the single-conical-shock inlet are provided.
Date: December 1, 1953
Creator: Haefeli, Rudolph C. & Bernstein, Harry
Partner: UNT Libraries Government Documents Department

Normal Accelerations and Associated Operating Conditions on Four Types of Commercial Transport Airplanes From VGH Data Available as of September 1951

Description: Memorandum presenting results obtained from time-history records of normal accelerations, airspeed, and altitude. Additional data have been obtained from the operations of two types of commercial transport airplanes together with data on two other types of transport airplanes.
Date: May 19, 1952
Creator: Steiner, Roy & Persh, Doris A.
Partner: UNT Libraries Government Documents Department

Performance of Isentropic Nose Inlets at Mach Number of 5.6

Description: Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all of the configurations yielded larger total-pressure recoveries than had previously been obtianed with a single-conical-shock inlet. Results regarding the flow about the forebody and performance comparisons are provided.
Date: May 6, 1954
Creator: Bernstein, Harry & Haefeli, Rudolph C.
Partner: UNT Libraries Government Documents Department

A Preliminary Investigation of Combustion With Rotating Flow in an Annular Combustion Chamber

Description: Memorandum presenting a preliminary investigation of flame-stability and flame-extinction characteristics of a propane-air mixture in an annular combustion chamber conducted with both straight and rotational flow. The rotating mixture burned at higher axial-inlet stream velocities and with more stable flames than could be obtained with straight-flow burning.
Date: September 18, 1951
Creator: Schwartz, Ira R.
Partner: UNT Libraries Government Documents Department

The Preparation, Physical Properties, and Heats of Combustion of Four Alkylsilanes

Description: Memorandum presenting a group of alkylsilanes consisting of monoethylsilane, diethylsilane, and trimethylsilane prepared in 65- and 90-percent yield by reduction of the respective alkylchlorosilanes with either lithium hydride or lithium aluminum hydride. The boiling points, densities, refractive indices, and freezing points were determined and presented with a survey of literature values.
Date: March 8, 1951
Creator: Tannenbaum, Stanley & Murphy, Maurice F.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Chemical Starting Technique for the Acid - Gasoline Rocket Propellant System

Description: Memorandum presenting an investigation of the use of a small quantity of fluid that ignites spontaneously within nitric acid to initiate the acid-gasoline reaction carried out in a 200-pound-thrust uncooled engine with a characteristic length of 30 inches at a range of temperatures. The starting process was divided into two phases: ignition and transition. Results regarding ignition temperature limits, effect of temperature on allowable igniter fuel flow, optimum valve opening time for ignition, effect of temperature on transition process, effect of running-fuel reactivity on transition, and tar-forming tendencies of igniter fuels are provided.
Date: January 30, 1953
Creator: Hennings, Glen & Morrell, Gerald
Partner: UNT Libraries Government Documents Department

Preliminary Investigation at Low Speeds of Swept Wings in Yawing Flow

Description: Memorandum presenting a wind-tunnel investigation conducted to determine the rotary stability characteristics in yawing flow of a series of untapered wings with angles of sweep of -45, 0, 45, and 60 degrees. The results of the yawing-flow tests indicated that the values of the rotary derivatives agreed fairly well with simple sweep theory for a moderate range of lift coefficients.
Date: February 4, 1948
Creator: Goodman, Alex & Feigenbaum, David
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

Analytical Investigation of Ram-Jet-Engine Performance in Flight Mach Number Range From 3 to 7

Description: "An analytical investigation was made of the performance of isolated ram-jet engines in the flight Mach number range from 3 to 7 for two types of diffuser, a high-efficiency diffuser, and a normal-shock diffuser. The fuel was assumed to be a hydrocarbon similar to gasoline. The conclusions reached are: (1) a design altitude of about 100,000 feet is desirable for a high-efficiency high Mach number ram jet on the basis of engine construction and performance; and (2) although greater thrust could be obtained with other fuels, gasoline provides sufficient energy release for maximum engine efficiency in the flight Mach number range investigated. The maximum engine efficiency calculated was 0.47, which occurred at a Mach number of 5. At a Mach number of 7, the maximum propulsive-thrust coefficient was 0.57" (p. 1).
Date: October 17, 1951
Creator: Evans, Philip J., Jr.
Partner: UNT Libraries Government Documents Department

Effective Thermal Conductivities of Magnesium Oxide Stainless Steel, and Uranium Oxide Powders

Description: Memorandum presenting testing conducted to determine the conductivity of magnesium oxide, stainless steel, and uranium oxide powders in various gases at a range of temperatures. Results regarding the experimental effective conductivities, comparison of analytical and experimental results, and effect of pressure on conductivity are provided.
Date: October 29, 1953
Creator: Eian, C. S. & Deissler, R. G.
Partner: UNT Libraries Government Documents Department

Measurements of Normal-Force-Coefficient Fluctuation on Four 9-Percent-Thick Airfoils Having Different Locations of Maximum Thickness

Description: Memorandum presenting a two-dimensional wind-tunnel investigation of the effects of maximum-thickness location on fluctuating pressures and normal-force coefficients on 9-percent-thick airfoils, which indicated that for normal-force coefficients up to 0.6, the section variables had little effect on the pressure pulsations and root-mean-square normal-force-coefficient fluctuations. Results regarding pressure fluctuations and normal-force-coefficient fluctuations are provided.
Date: April 27, 1954
Creator: Humphreys, Milton D.
Partner: UNT Libraries Government Documents Department