The aerodynamic design and performance analysis of two exhaust nozzles considered for use on a vehicle following an accelerating flight profile to a maximum flight speed corresponding to Mach 4.2 is presented. The vehicle operational requirements were set by the Air Vehicle Baseline Study commissioned by the Office of Naval Research. An afterburning engine cycle was assumed in the design and analysis process. The two nozzles investigated here were an axisymmetric convergent-divergent (C-D) nozzle with variable throat and exit area and an isentropic plug nozzle with variable throat area enabled by a translating outer cowl. Computational fluid dynamics was used to assist in the design process and to investigate the installed performance of th...
Superior performance levels of advanced fighter aircraft require highly integrated nozzles with thru...
The overall performance of a scramjet-powered vehicle not only depends on the performance of individ...
A method is proposed for the aerodynamic design of nozzles with uniform outflow for supersonic and h...
The design of a nozzle of an unfueled quasi-axisymmetric scramjet model is optimized for minimum dra...
For the past several decades, research dealing with hypersonic flight regimes has been restricted ma...
The development of rocket based combined cycle (RBCC) engines is highly dependent upon integrating s...
Most fighters use the convergent-divergent nozzle configuration to accelerate into the supersonic re...
The objective of this program was to conduct an experimental and analytical evaluation of low noise ...
The exhaust nozzle is an integral part of a jet engine and critical to its overall system performanc...
The current paper discusses aerodynamic exhaust nozzle technology challenges for aircraft and space ...
The optimization of 2D expansion lines and key parameters of three-dimensional configurations was ca...
A nozzle is a relatively simple device that consists of a specifically formed tube that allows hot g...
A nozzle shape optimization study for a quasi-axisymmetric scramjet has been performed for a Mach 7....
A comprehensive understanding of the interplay between airframe aerodynamics and propulsion system i...
International audienceThe aim of this paper is to discuss the development of new contours of axisymm...
Superior performance levels of advanced fighter aircraft require highly integrated nozzles with thru...
The overall performance of a scramjet-powered vehicle not only depends on the performance of individ...
A method is proposed for the aerodynamic design of nozzles with uniform outflow for supersonic and h...
The design of a nozzle of an unfueled quasi-axisymmetric scramjet model is optimized for minimum dra...
For the past several decades, research dealing with hypersonic flight regimes has been restricted ma...
The development of rocket based combined cycle (RBCC) engines is highly dependent upon integrating s...
Most fighters use the convergent-divergent nozzle configuration to accelerate into the supersonic re...
The objective of this program was to conduct an experimental and analytical evaluation of low noise ...
The exhaust nozzle is an integral part of a jet engine and critical to its overall system performanc...
The current paper discusses aerodynamic exhaust nozzle technology challenges for aircraft and space ...
The optimization of 2D expansion lines and key parameters of three-dimensional configurations was ca...
A nozzle is a relatively simple device that consists of a specifically formed tube that allows hot g...
A nozzle shape optimization study for a quasi-axisymmetric scramjet has been performed for a Mach 7....
A comprehensive understanding of the interplay between airframe aerodynamics and propulsion system i...
International audienceThe aim of this paper is to discuss the development of new contours of axisymm...
Superior performance levels of advanced fighter aircraft require highly integrated nozzles with thru...
The overall performance of a scramjet-powered vehicle not only depends on the performance of individ...
A method is proposed for the aerodynamic design of nozzles with uniform outflow for supersonic and h...