174 Matching Results

Search Results

Results: 1 - 24 next
open access

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Description: "A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department
open access

Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Description: Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date: May 9, 1955
Creator: Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of the Effects of Angle of Attack on the Pressure Recovery of a Circular Nose Inlet With Several Lip Shapes

Description: Note presenting wind-tunnel tests to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0 to 25 degrees.
Date: May 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department
open access

A technique utilizing rocket-propelled test vehicles for the measurement of the damping in roll of sting-mounted models and some initial results for delta and unswept tapered wings

Description: Report presenting a free-flight test technique that can be used to obtain damping in roll of sting-mounted wings and wing-fuselage combinations over high subsonic, transonic, and supersonic speeds with rocket-propelled test vehicles. Results regarding delta wings and unswept tapered wings are provided.
Date: May 1955
Creator: Bland, William M., Jr. & Sandhal, Carl A.
Partner: UNT Libraries Government Documents Department
open access

Theory of the Jet Syphon

Description: Note presenting a new approach to the theory of the mixing of two currents in an injector which deals with an incompressible ideal fluid. The theory shows new potentialities in an appropriate shaping of the form of the walls of the mixing zone so as to improve the jet-syphon efficiency beyond the heretofore theoretically predicted. A few examples of ways to improve jet-syphon efficiency are indicated.
Date: May 1955
Creator: Szczeniowski, B.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Properties of High-Temperature Brazed Joints Processed in Vacuum or in Molten Salt

Description: Report presenting an investigation to determine the shear strengths of high-temperature-alloy blazed joints. The variables investigated included the method of brazing, nickel addition to the brazing alloy, brazing temperature, holding time at temperature, and a protective coating on the braze area for salt-bath specimens. Results regarding individual phases and the microstructure of brazed joints are provided.
Date: May 1955
Creator: Gyorgak, C. A. & Francisco, A. C.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Fully Developed Turbulent Heat Transfer and Flow in an Annulus With Various Eccentricities

Description: From Introduction: "Most of the existing analyses for turbulent flow and heat transfer in passages have been confined to circular tubes or parallel plates (refs. 1 to 5). In reference 6, temperature distributions for rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients. Some work on the calculation of the velocity and shear-stress distributions in corners is reported in reference 7."
Date: May 1955
Creator: Deissler, Robert G. & Taylor, Maynard F.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Jet-Engine Noise Reduction by Screens Located Transversely Across the Jet

Description: Note presenting an investigation of screens placed transversely across the jet as a noise-reduction device on a full-scale turbojet engine to determine the effect on the sound field of screen mesh, wire diameter, and screen location. The investigation showed that the screens, when properly placed, lower the noise level in the area downstream of the jet exit and increase it upstream.
Date: May 1955
Creator: Callaghan, Edmund E. & Coles, Willard D.
Partner: UNT Libraries Government Documents Department
open access

Longitudinal turbulent spectrum survey of boundary layers in adverse pressure gradients

Description: Report presenting measurements of the longitudinal turbulent spectra for four stations in a turbulent boundary layer with increasing adverse pressure gradients in tabular form. Frequency diagrams show a decrease in the percentage of energy density contained in the high-frequency range as the flow continued downstream against an adverse pressure gradient.
Date: May 1955
Creator: Sandborn, Virgil A. & Slogar, Raymond J.
Partner: UNT Libraries Government Documents Department
open access

Effect of Pressure on Thermal Conductance of Contact Joints

Description: Technical note presenting tests conducted to determine the factors influencing the thermal conductance across the interface formed between stationary plane surfaces of 75S-T6 aluminum-alloy and AISI Type 416 stainless-steel blocks. The types of joints investigated included bare metal-to-metal contact, contact surfaces separated by a good conductor (brass), and contact surfaces separated by a thin sheet of insulation (asbestos). Results regarding the effect of surface roughness, pressure, mean i… more
Date: May 1955
Creator: Barzelay, Martin E.; Tong, Kin Nee & Holloway, George F.
Partner: UNT Libraries Government Documents Department
open access

Effect of a Discontinuity on Turbulent Boundary-Layer-Thickness Parameters With Application to Shock-Induced Separation

Description: Note presenting an analysis of the problem of shock-induced turbulent boundary-layer separation by an approximate method. The method is based on a moment-of-momentum equation and calculates the change of boundary-layer-thickness parameter sand form factor caused by a discontinuity where the effects of friction can be neglected. The form of the result suggests that the Mach number ratio across the shock is a characteristic parameter for defining shock-induced separation.
Date: May 1955
Creator: Reshotko, Eli & Tucker, Maurice
Partner: UNT Libraries Government Documents Department
open access

On the calculation of the 1 (center dot) P oscillating aerodynamic loads on single-rotation propellers in pitch on tractor airplanes

Description: Report presenting a simplified procedure to calculate the 1-P oscillating aerodynamic thrust loads on single-rotation propellers in pitch at zero yaw on tractor airplanes. The application of the procedure requires only a knowledge of upflow angles at the horizontal center line of the propeller disk.
Date: May 1955
Creator: Rogallo, Vernon L. & Yaggy, Paul F.
Partner: UNT Libraries Government Documents Department
open access

Some calculations of the lateral response of two airplanes to atmospheric turbulence with relation to the lateral snaking problem

Description: Report presenting calculations of the lateral response to representative time histories of atmospheric turbulence for two airplanes with widely different dynamic properties and explanations for their differences in behavior. The results indicate that atmospheric turbulence can cause and maintain a lateral hunting oscillation of a plane, which can be fairly regular and more pronounced for lightly damped airplanes. This may explain some of the cases of airplane snaking that have not been explaine… more
Date: May 1955
Creator: Bird, John D.
Partner: UNT Libraries Government Documents Department
open access

Effect of Oxygen Content of Furnace Atmosphere on Adherence of Vitreous Coatings to Iron

Description: Note presenting a series of vitreous coatings of the same basic composition, but with cobalt-oxide contents varying from 0 to 6.4 percent by weight, which was fired on ingot iron in atmospheres consisting of various oxygen-nitrogen mixtures. Results of the investigation showed that a decrease in the amount of oxygen in the firing atmosphere necessitated an increase in the amount of cobalt oxide in the enamel if optimum adherence was to be secured.
Date: May 1955
Creator: Eubanks, A. G. & Moore, D. G.
Partner: UNT Libraries Government Documents Department
open access

Measurements of free-space oscillating pressures near a propeller at flight Mach numbers to 0.72

Description: Report presenting a series of measurements at three stations of the oscillating pressures near the propeller at flight Mach numbers up to 0.72. The measurements were made at a single radial station and three axial positions. Results regarding effect of engine speed at constant flight Mach number and power and effect of flight Mach number at constant engine speed and power are provided.
Date: May 1955
Creator: Vogeley, Arthur W. & Kurbjun, Max C.
Partner: UNT Libraries Government Documents Department
open access

On the Kernel function of the integral equation relating lift and downwash distributions of oscillating wings in supersonic flow

Description: From Summary: "This report treats the Kernel function of the integral equation that relates a known or prescribed downwash distribution to an unknown lift distribution for harmonically oscillating wings in supersonic flow. The treatment is essentially an extension to supersonic flow of the treatment given in NACA report 1234 for subsonic flow. For the supersonic case the Kernel function is derived by use of a suitable form of acoustic doublet potential which employs a cutoff or Heaviside unit f… more
Date: May 1955
Creator: Watkins, Charles E. & Berman, Julian H.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Ear Formation in Deep-Drawn Cups

Description: From Introduction: "The purpose of this paper is to show that the number and location of ears can be computed on the basis of single-crystal behavior and a knowledge of the orientation of the polycrystalline aggregate. Although the proposed method is a general one, only face-centered cubic metals are considered in this paper."
Date: May 1955
Creator: McEvily, Arthur J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Hovering flight tests of a four-engine-transport vertical take-off airplane model utilizing a large flap and extensible vanes for redirecting the propeller slipstream

Description: Report presenting an investigation of the take-off, landing, and hovering-flight characteristics of a four-engine-transport, vertical take-off airplane with a remotely controlled free-flight model. The model had four propellers distributed along the wing with thrust axes parallel to the fuselage axis. Results regarding hovering flight at altitude, hovering flight near the ground, take-offs and landings, and preliminary tests with lower vanes installed are provided.
Date: May 1955
Creator: Tosti, Louis P. & Davenport, Edwin E.
Partner: UNT Libraries Government Documents Department
open access

An NACA vane-type angle-of-attack indicator for use at subsonic and supersonic speeds

Description: From Summary: "A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented together with a discussion of the corrections to be applied to the indicated readings."
Date: May 1955
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of Aerodynamic Characteristics of Small Inclined Air Outlets at Transonic Mach Numbers

Description: "The aerodynamic characteristics of several outlets with inclined or curved axes discharging air into a transonic stream have been investigated. The data presented herein show the discharge coefficient of such outlets and the static-pressure distribution in the vicinity of the outlets for several values of stream Mach number and discharge flow parameter. Tuft observations, showing the vortex formations caused by the outlet discharge from a perpendicular and an inclined outlet, are also presente… more
Date: May 1955
Creator: Dewey, Paul E.
Partner: UNT Libraries Government Documents Department
open access

Total Lift and Pitching Moment on Thin Arrowhead Wings Oscillating in Supersonic Potential Flow

Description: Note presenting expressions based on linearized supersonic potential theory for the total lift and moment coefficients of thin arrowhead wings oscillating in pitch and vertical translation. The arrowhead plan form as treated herein includes all pointed-tip wings; the delta plan form with an unswept trailing edge is a special case. Results regarding the effects of Mach number, plan form, and pitch-axis location and comparisons with other work are provided.
Date: May 1955
Creator: Cunningham, H. J.
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot

Description: Note presenting a portion of a theoretical analysis to determine the feasibility of using a proportional-plus-flicker automatic pilot for stabilization and control of a supersonic canard airframe. The autopilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control.
Date: May 1955
Creator: Seaberg, Ernest C.
Partner: UNT Libraries Government Documents Department
open access

The Zero-Lift Wave Drag of a Particular Family of Unswept, Tapered Wings With Linearly Varying Thickness Ratio

Description: Report presenting the zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio and symmetrical parabolic-arc sections. It is found that the variable-thickness-ratio wings can be used to advantage with no serious structural penalties if the wings have the same given root thickness ratio or internal volume. Results regarding the given frontal area and given volume are provided.
Date: May 1955
Creator: Henderson, Arthur, Jr. & Goodwin, Julia M.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen