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Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system

Description: The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date: October 23, 1951
Creator: Armstrong, John C.
Item Type: Refine your search to only Report
open access

Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05

Description: Report presenting flight test data obtained with two Bell X-1 airplanes, one with an 8-percent-thick wing and a 6-percent-thick tail and one with a 10-percent-thick wing and an 8-percent-thick tail. Data was obtained at a variety of Mach numbers, lift coefficients, and test altitudes. Results regarding stick-fixed stability and trim changes are provided.
Date: October 9, 1951
Creator: Drake, Hubert M.; Carden, John R. & Clagett, Harry P.
Item Type: Refine your search to only Report
open access

An Analytic Determination of the Flow Behind a Symmetrical Curved Shock in a Uniform Stream

Description: From Introduction: "The present report is concerned with a closer investigation of the validity of this method and includes a more complete formulation, as well as the computation procedure, of the series expansion. As stated in reference 1, the flow thus determined depends only on the Mach number when the detached distance is adopted as the length scale. General formulas and the procedure of calculation are given in this report for such purposes."
Date: October 1951
Creator: Lin, C. C. & Shen, S. F.
Item Type: Refine your search to only Report
open access

Analytical Chemistry Division Quarterly Progress Report for Period Ending March 26, 1951

Description: Technical report covering experiments happening on the Analytical Chemistry Division's sites at the Oak Ridge National Laboratory. Includes information on ionic analyses, radio-chemical analyses, spectrochemical analyses, service analyses, inorganic preparations, analytical chemical control of homogeneous reactor solution, optical and electron microscopy, and service analyses for the period ending March 26, 1951. [From Abstract]
Date: October 8, 1951
Creator: Kelley, M. T. & Susano, C. D.
Item Type: Refine your search to only Report
open access

Analytical investigation of flow through high-speed mixed-flow turbine

Description: From Introduction: "Good experimental correlation of the analytical results was obtained for the compressor even though isentropic flow and axial symmetry were assumed (reference 1). In order to determine the flow through the turbine being investigated, however, it was necessary to extend the method of reference 1 to include the flow downstream of the rooter since the large blade taper and hub-shroud curvature caused downstream conditions which affected the flow inside the rotor."
Date: October 3, 1951
Creator: Stewart, Warner L.
Item Type: Refine your search to only Report
open access

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 … more
Date: October 17, 1951
Creator: Evans, Philip J., Jr.
Item Type: Refine your search to only Report
open access

Application of Heavy Media Separation, Flotation and Carbonate Leaching to Congo Ores

Description: The investigation of magnesitic-dolomite uranium ores from Union Miniere du Haute Katanga, Belgian Congo, was undertaken in order to examine the possibility of separating the uranium minerals from the carbonate minerals by Heavy Media Separation or froth flotation; thus reducing the sulfuric acid consumption during the uranium leach. In addition, the effect of carbonate leaching the whole ore and carbonate flotation products was examined.
Date: October 31, 1951
Creator: Breymann, John B.
Item Type: Refine your search to only Report
open access

Base pressures measured on several parabolic-arc bodies of revolution in free flight at Mach numbers from 0.8 to 1.4 and at large Reynolds numbers

Description: Report presenting base pressures measured on several fin-stabilized bodies of parabolic-arc profile in free flight at a range of Mach and Reynolds numbers. The bodies varied in length but had the same afterbody ratios. Results regarding base pressure coefficients, side pressure coefficients, effect of afterbody length, and drag are provided.
Date: October 26, 1951
Creator: Katz, Ellis & Stoney, William E., Jr.
Item Type: Refine your search to only Report
open access

Calculation of Higher Approximations for Two-Dimensional Compressible Flow by a Simplified Iteration Process

Description: Note presenting the development of iteration equations for a simplified solution of the nonlinear compressible-flow equation and its application to two profiles, the ellipse and the Kaplan section. Limitations imposed on the solutions by simplifications in the differential equation and the boundary conditions are discussed.
Date: October 1951
Creator: Braun, W. H. & Klein, M. M.
Item Type: Refine your search to only Report
open access

Characteristics of a Transonic Test Section With Various Slot Shapes in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting a large wind tunnel that has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of a slotted wind tunnel has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality can be produced.
Date: October 18, 1951
Creator: Wright, Ray H. & Ritchie, Virgil S.
Item Type: Refine your search to only Report
open access

Compilation of data on 51 ruptured slugs

Description: The following tabulation includes information on all uranium slug failures which have occurred through September 26, 1951. The four suspect slugs which are listed were discharged from tubes which gave strong indication of containing ruptures. Although no obvious rupture could be found among the slugs from these tubes, the listed pieces exhibited defects which may be incipient ruptures.
Date: October 4, 1951
Creator: O'Keefe, D.P.
Item Type: Refine your search to only Report
open access

Damping in Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio

Description: "Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the on… more
Date: October 8, 1951
Creator: Sanders, E. Claude, Jr. & Edmondson, James L.
Item Type: Refine your search to only Report
open access

Damping in Roll of Straight and 45 Degree Swept Wings of Various Taper Ratios Determined at High Subsonic, Transonic, and Supersonic Speeds With Rocket-Powered Models

Description: Report presenting rocket-powered flight testing to determine the damping in roll of several wings of 0 degree and 45 degree quarter-chord-line sweep with various taper ratios for a range of Mach numbers. Damping in roll decreased with decreasing taper ratio at roughly the same rate for swept and unswept wings and also decreased by sweeping the quarter-chord line. The experimental results were also consistently lower than what was predicted by theory.
Date: October 10, 1951
Creator: Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
open access

Deplacement Effect of the Laminar Boundary Layer and the Pressure Drag

Description: The displacement effect of the boundary layer on the outer frictionless flow is discussed for both steady and unsteady flows. The analysis is restricted to cases in which the potential flow pressure distribution remains valid for the boundary-layer calculation. Formulas are given for the dependence of the pressure drag, friction drag, and total drag of circular cylinders on the time from the start of motion for cases in which the velocity varies as a power of the time. Formulas for the location… more
Date: October 1951
Creator: Görtler, H.
Item Type: Refine your search to only Report
open access

Derivation of the Equations of Motion of a Symmetrical Wing-Tip-Coupled Airplane Configuration With Rotational Freedom at the Junctures

Description: "The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).
Date: October 8, 1951
Creator: Schy, Albert A.
Item Type: Refine your search to only Report
open access

Dynamic Stability and Control Characteristics of a Delta-Wing Vertically Rising Airplane Model in Take-Offs, Landings, and Hovering Flight

Description: Report presenting an investigation by means of tests of a flying model in still air to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane in take-off, landing, and hovering phases of flight. The uncontrolled pitching motion consisted of an unstable oscillation which was more unstable with a rearward than with the normal center-of-gravity location.
Date: October 9, 1951
Creator: Lovell, Powell M., Jr.; Bates, William R. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
open access

Effect of Angle of Attack and Exit Nozzle Design on the Performance of a 16-Inch Ram Jet at Mach Numbers From 1.5 to 2.0

Description: "An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a gr… more
Date: October 5, 1951
Creator: Perchonok, Eugene; Wilcox, Fred & Pennington, Donald
Item Type: Refine your search to only Report
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