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High Pressure Low Resistance Joint

Description: The following report describes the usage of tin-foil to obtain a mechanical joint of low electrical resistance while providing a seal to hold water at a pressure of 300 psi.
Date: March 28, 1955
Creator: Peters, Ralph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Description: Report presenting a full-scale, free-jet investigation to determine the performance of a side-inlet supersonic diffuser designed for a flight Mach number of 2.75. Several internal modifications made to improve diffuser-outlet flow uniformity were also evaluated. Results regarding the general characteristics of the diffuser and effect of diffuser modifications on flow distribution are provided.
Date: March 28, 1955
Creator: Farley, John M. & Seashore, Ferris L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of a supersonic compressor with swept and tilted diffuser blades

Description: Report presenting testing of a supersonic mixed-flow compressor of large weight-flow capacity with a stator with swept and tilted blades was tested over a range of air tip speeds. As rotor speed increased, stage efficiency decreased continuously. Results regarding the overall compressor performance, flow fluctuations, and static-pressure distribution are provided.
Date: March 28, 1955
Creator: Goldstein, Arthur W. & Schacht, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Pressure-Jet Power Plant for Helicopter

Description: From Introduction: "In comparison with the shaft-driven rotor, the jet rotor is shown in references 1 and 2 to provide direct reductions in helicopter empty weight and to increase the pay-load capacity by (1) eliminating the gear-reduction train between the rotor shaft and the power plant, (2) eliminating the antitorque tail rotor, and (3) using a power plant of low specific weight."
Date: March 28, 1955
Creator: Krebs, Richard P. & Miller, William S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 1: design, over-all performance, and rotating-stall characteristics

Description: Report presenting a transonic compressor rotor with double-circular-arc blade sections, which was designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio and to obtain more blade-element data. Results regarding overall performance, rotor-inlet conditions, rotor-outlet conditions, and rotating-stall characteristics and blade vibrations are provided.
Date: March 28, 1955
Creator: Tysl, Edward R.; Schwenk, Francis C. & Watkins, Thomas B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Interferometric observation of flow about an isentropic (reverse Prandtl-Meyer streamline) compression wedge at Mach 3.0

Description: Report presenting an interferometric study of the flow over a two-dimensional isentropic compression surface at a Mach number of 3.0. The flow field was essentially that of a strong-branch-shock configuration resulting from a surface flow turning that corresponded to an empirical limiting value of free-stream normal-shock pressure rise.
Date: March 28, 1955
Creator: Connors, James F.; Woollett, Richard R. & Blue, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental performance of the mixed-oxides-of-nitrogen-ammonia propellant combination in a 1000-pound-thrust rocket engine

Description: An investigation of the performance of the mixed-oxides-of-nitrogen-ammonia propellant combination over a range of conditions with several injectors. Results regarding specific impulse, characteristic velocity, and thrust coefficient as functions of oxidant-fuel weight ratio are provided.
Date: March 28, 1955
Creator: Tomazic, William A. & Kinney, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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