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Altitude Starting Tests of a Small Solid Propellant Rocket

Description: From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date: June 21, 1957
Creator: Sloop, John L. & Krawczonek, Eugene M.
open access

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbines for Turbojet Engines 2: Analytical Techniques

Description: Memorandum presenting computation methods for analyzing turbojet-engine performance for a series of air-cooled nonafterburning and afterburning engines where all the engine components are simultaneously aerodynamically limited. The coolant-flow ratio was arbitrarily assigned so that the results of the analysis can be applied to any specific air-cooled blade configurations.
Date: June 21, 1954
Creator: Rossbach, Richard J.
open access

Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Description: Report presenting an extension of previous work on immersed surfaces in the combustion zone of a ramjet engine. The primary focus was to determine the effect of combustion efficiency and stability of blades located within the immediate wake of a V-gutter flame holder and to find some location and orientation of blades for optimum combustion efficiency and improved stability limits with a minimum of pressure loss.
Date: June 21, 1954
Creator: Reynolds, Thaine W. & Male, Donald W.
open access

Effect of Nozzle Contour on Drag of Parabolic Afterbodies

Description: Memorandum presenting an investigation of the effect of nozzle internal contour on afterbody drag in the 8- by 6-foot supersonic wind tunnel. Five different nozzle-afterbody configurations were evaluated. Results regarding the boattail pressure drag, base drag, and total drag are provided.
Date: June 21, 1954
Creator: Vargo, Donald J. & Englert, Gerald W.
open access

An Integrated Miniature Solvent Extraction System for Processing Radioactive Solutions

Description: Abstract: "Because of the radiation hazards inherent in processing large volumes of radioactive solutions by solvent extraction techniques, there is need for a system with small hold-up which can be contained within a minimum of shielding and yet which is versatile enough to be used as a research tool. A system utilizing a miniature mixer-settler has been constructed and its successful operation by remote means demonstrated. The unit is semiportable and employs a number of novel features of val… more
Date: June 21, 1955
Creator: Bloom, Justin L.
open access

Meteorological Problems Associated With Commercial Turbojet-Aircraft Operation

Description: Memorandum presenting an analysis and evaluation of the meteorological requirements and problems anticipated with the operation of commercial turbojet aircraft. Discussions concerning problems of temperature, wind, pressure, ceiling, visibility, cloud and clear-air turbulence, icing, and communication are included in this study.
Date: June 21, 1955
Creator: Working Group of the NACA Subcommittee on Meteorological Problems
open access

Thermal Annealing Kinetics of Interlayer Spacing Damage in Irradiated Graphite

Description: The primary objective of this work is to add to the understanding of irradiated graphite. This report describes an experimental technique whereby changes in crystal lattice parameter may be studied as a function of time at constant temperature. The results given here are limited to changes in the C₀ spacing for a typical sample of irradiated graphite in the temperature range 100 to 750 C.
Date: June 21, 1955
Creator: Nightingale, R. E.
open access

Velocity Distributions Measured in the Slipstream of Eight-Blade and Six-Blade Dual-Rotating Propellers at Zero Advance

Description: Report presenting an investigation of NACA 8.75-(5)(05)-037 eight- and six-blade dual-rotating propellers under static conditions. The slipstream-boundary cone angle was found to agree with the theoretical angle of spread for an unheated jet. Results regarding the longitudinal survey, stationary survey, effect of blade angle, nature of flow near propeller, and effect of blade angle on slipstream rotation are provided.
Date: June 21, 1955
Creator: Salters, Leland B., Jr.
open access

A Wind-Tunnel Investigation of the Use of Spoilers for Obtaining Static Longitudinal Stability of a Canard-Missile Model in Reverse Flight

Description: Report presenting an investigation in the stability tunnel of the use of spoilers for obtaining static longitudinal stability of a model of a canard missile in reverse flight. Results indicated that stable pitching-moment slopes can be obtained at angles of attack up to 11 degrees in the low speed range of the tests, but further investigation of high subsonic speeds will be necessary.
Date: June 21, 1954
Creator: Fletcher, Herman S.
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