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Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 1: conical spike all-external compression inlet with subsonic cowl lip

Description: Report presenting an experimental investigation to determine the force and pressure characteristics of a typical nose inlet ramjet configuration. It consisted of a conical spike all-external compression inlet attached to an annular subsonic diffuser. Results regarding external-flow characteristics and internal-flow characteristics are provided.
Date: January 19, 1951
Creator: Esenwein, Fred T. & Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth

Description: Report presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratios of cooling air to combustion gas, and pressure altitudes. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of the wire cloth are provided.
Date: August 19, 1954
Creator: Koffel, William K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The near noise field of static jets and some model studies of devices for noise reduction

Description: An experimental study is presented of the pressure fluctuations near jet exhaust streams made during unchoked operation of a turbojet engine and a 1-inch-diameter high-temperature model jet and during choked operation of various sizes of model jets with unheated air. The tests for unchoked operation indicate a random spectrum of rather narrow band width which varies in frequency content with axial position along the jet. Pressure surveys from the model tests along lines parallel to the 15 degre… more
Date: February 19, 1954
Creator: Lassiter, Leslie W. & Hubbard, Harvey H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation at Mach number 1.9 of simulated wing-root inlets

Description: Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.
Date: January 19, 1955
Creator: Piercy, Thomas G. & Weinstein, Maynard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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