Results 81 to 90 of about 2,502 (163)

Advanced supersonic propulsion study, phase 3 [PDF]

open access: yes
The variable stream control engine is determined to be the most promising propulsion system concept for advanced supersonic cruise aircraft. This concept uses variable geometry components and a unique throttle schedule for independent control of two flow
Howlett, R. A.   +3 more
core   +1 more source

Tandem Fan Applications in Advanced STOVL Fighter Configurations [PDF]

open access: yes
The series/parallel tandem fan engine is evaluated for application in advanced STOVL supersonic fighter aircraft. Options in engine cycle parameters and design of the front fan flow diverter are examined for their effects on engine weight, dimensions ...
Eskey, Megan A.   +2 more
core   +1 more source

Ablative response of a silica phenolic to simulated liquid propellant rocket engine operating conditions [PDF]

open access: yes
Ablative response of silica phenolic to simulated liquid propellant rocket engine operating ...
Moyer, C. B.   +3 more
core   +1 more source

The NASA research program on propulsion for supersonic cruise aircraft [PDF]

open access: yes
The objectives and status of the propulsion portion of a program aimed at advancing the technology and establishing a data base appropriate for the possible future development of supersonic cruise aircraft are reviewed.
Weber, R. J.
core   +1 more source

Free-jet investigation of mechanically suppressed, high radius ratio coannular plug model nozzles [PDF]

open access: yes
The experimental and analytical acoustic results of a scale-model investigation or unsuppressed and mechanically suppressed high-radius ratio coannular plug nozzles with inverted velocity and temperature profiles are summarized.
Brausch, J. F.   +3 more
core   +1 more source

Variable stream control engine concept for advanced supersonic aircraft: Features and benefits [PDF]

open access: yes
The Variable Stream Control Engine is studied for advanced supersonic cruise aircraft. Significant environmental and performance improvements relative to first generation supersonic turbojet engines are cited.
Howlett, R. A.
core   +1 more source

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