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Investigation of an NACA Submerged Inlet at Mach Numbers from 1.17 to 1.99

Description: Memorandum presenting an investigation conducted with an NACA submerged inlet at Mach numbers from 1.17 to 1.99. Total-pressure ratio, mass-flow ratio, and static pressure distribution along the ramp and main body were obtained at angles of attack of 0 and 6 degrees for a side inlet location. The results showed that the maximum total-pressure ratio attainable with the submerged inlet decreased from 0.83 at a Mach number of 1.17 to 0.52 at a Mach number of 1.99.
Date: September 15, 1952
Creator: Anderson, Warren E. & Frazer, Alson C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet

Description: Report presenting an investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles through a range of Mach numbers by use of a transonic bump. Results regarding the ram-recovery ratio, pressure distributions, and tuft studies are provided.
Date: June 5, 1950
Creator: Axelson, John A. & Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Development of NACA submerged inlets and a comparison with wing leading-edge inlets for a 1/4-scale model of a fighter airplane

Description: Characteristics of NACA submerged duct entries and wing leading-edge inlets designed for a 1/4 scale flow model of a fighter-type airplane powered by a jet engine in the fuselage are presented.
Date: August 7, 1947
Creator: Mossman, Emmet A. & Gault, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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