Secondary injection fluidic thrust vectoring of an axisymmetric supersonic nozzle
type: Dataset
description: Secondary injection into the divergent section of a supersonic rocket nozzle is investigated for the fluidic thrust vectoring effects. The study was conducted in the framework of CNES PERSEUS program and was motivated by the need for an alternative vectoring solution aimed for a small space launcher. The thesis work, based on the combined experimental and numerical approaches, essentially comprises of a wide parametric study mainly concerning the position of the injection, the shape of the primary and injection nozzles, flow regime, gas thermophysical properties and injected fluid mass-flow-rate. The analysis shows that for some optimal configurations, pertinent deflection angles can be obtained using the moderate injection rates. Furthermore, the study was extended to the hot flow multi-species investigation, simulating a case closer to the real applications. This numerical analysis indicated that the fluidic vectoring method remains effective with injection of combustion products into the divergent section of a propulsive rocket nozzle.
landing page: https://theses.hal.science/tel-00872072
identifier: NNT: 2013ORLE2010
keyword: decollement
keyword: ecoulement-transversal-supersonique
keyword: flow-separation
keyword: force-laterale-aerodynamique
keyword: infoeu-reposemanticsdoctoralthesis
keyword: interaction-de-choc
keyword: rocket-nozzle
keyword: shock-interaction
keyword: side-loads
keyword: spiotherengineering-sciences-physicsother
keyword: supersonic-cross-flows
keyword: theses
keyword: thrust-vectoring
keyword: tuyere-propulsive
keyword: vectorisation-de-la-poussee
issued: 2026-05-09T09:56:45.021358
modified: 2026-05-09T09:56:45.021363
language: en
contact point: Organization
  fn: CCSD

test_moissonnage_selune
type: Agent

Secondary injection fluidic thrust vectoring of an axisymmetric supersonic nozzle
type: Distribution
format: HTML
access URL: https://theses.hal.science/tel-00872072
issued: 2026-05-09T09:56:45.030049
modified: 2026-05-09T09:56:45.005473