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Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations

Description: An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio r… more
Date: August 23, 1950
Creator: Jones, W. L.; Shillito, T. B. & Henzel, J. G., Jr.
Item Type: Refine your search to only Report
open access

Gas cooling of cylindrical control rods for pile Area ``G``: Preliminary report

Description: A first approximation of the gas required to cool control rods for Pile Area G is presented in the following report. Since the results are based on a number of assumptions and approximations, they should be considered only as a first approximation and subject to revision. A gadolinium-stainless steel control rod can probably be readily cooled by gas. A boron-stainless steel control rod would be difficult to cool with gas and would probably require about 1,000 lbs./hr. of helium per rod. Carbon … more
Date: March 23, 1950
Creator: Robbins, C. H.
Item Type: Refine your search to only Report
open access

Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube

Description: A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obt… more
Date: August 23, 1950
Creator: Lowdermilk, Warren H. & Grele, Milton D.
Item Type: Refine your search to only Report
open access

Interim report on pile graphite sampling production tests pile graphite expansion

Description: This report constitutes a summary and discussion of radiation damage to graphite and its effects on pile distortion. The data covered in this report consist of that obtained from some pile motion measurements and tube bowing measurements, but particularly of that information obtained from direct sampling of pile graphite.
Date: October 23, 1950
Creator: Warekois, E. P. & Reinker, P. H.
Item Type: Refine your search to only Report
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: A Pressure-Distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59

Description: Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.
Date: May 23, 1950
Creator: Cooper, Morton & Spearman, M. Leroy
Item Type: Refine your search to only Report
open access

Investigation of downwash and wake characteristics at a Mach number of 1.53 3: swept wings

Description: Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.
Date: February 23, 1950
Creator: Perkins, Edward W. & Canning, Thomas N.
Item Type: Refine your search to only Report
open access

Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section: Transonic-bump method

Description: Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.
Date: August 23, 1950
Creator: MacLeod, Richard G.
Item Type: Refine your search to only Report
open access

P-10 chemical equilibria

Description: Though the product of P-10 is T{sub 2}, the chief hazard is the tritium oxides, and tritium in water vapor might exchange with the hdyrogen in the water. If a catalyst is present, essentially all of the tritium would be exchanged. Because we do not know what catalyzers may exist at P-10 or in the lungs of a person breathing tritium, a ready answer cannot be given to the question of the importance of the exchange reactions. The HT + H{sub 2}O {r_reversible} HTO + H{sub 2} is also considered. The… more
Date: March 23, 1950
Creator: Roesch, W. C.
Item Type: Refine your search to only Report
open access

P-10 research program in biology

Description: Early this year recommendations for biological research with tritium were outlined by M. E. Getzendaner in document EW-17059. Since then work on many of the preliminary experiments suggested in that document has been and further thought has been given to design a research program to secure the information needed for evaluation of the tritium hazards. It seems desirable at this time to reformulate the projected research more extensively. This document will indicate only the scope of desirable in… more
Date: October 23, 1950
Creator: Thompson, R. C.
Item Type: Refine your search to only Report
open access

Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles

Description: "The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).
Date: May 23, 1950
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Sludge Acidification - Progress Report

Description: Report discussing the progress made on research concerning sluge-supernate acidification. This report focuses mainly on "'reverse strike' acidification and the observations of the physical characteristics of the test material," which was a synthetic incubated metal waste.
Date: June 23, 1950
Creator: Harmon, M. K.
Item Type: Refine your search to only Report
open access

Summary of Normal Accelerations, Gust Velocities, and Operating Practices, From April to August 1949 of a Twin-Engine Airplane in Commercial Transport Operations

Description: Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.
Date: August 23, 1950
Creator: Steiner, Roy & McDougal, Robert L.
Item Type: Refine your search to only Report
open access

Tests of a small-scale NACA submerged inlet at transonic Mach numbers

Description: Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provide… more
Date: February 23, 1950
Creator: Rolls, L. Stewart & Rathert, George A., Jr.
Item Type: Refine your search to only Report
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