Skip to Main content Skip to Navigation
Journal articles

Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection

Abstract : Transverse secondary gas injection into the supersonic flow of an axisymmetric convergent-divergent nozzle is investigated to describe the effects of the fluidic thrust vectoring within the framework of a small satellite launcher. Cold-flow dry-air experiments are performed in a supersonic wind tunnel using two identical supersonic conical nozzles with the different transverse injection port positions. The complex three-dimensional flow field generated by the supersonic cross-flows in these test nozzles was examined. Valuable experimental data were confronted and compared with the results obtained from the numerical simulations. Different nozzle models are numerically simulated under experimental conditions and then further investigated to determine which parameters significantly affect thrust vectoring. Effects which characterize the nozzle and thrust vectoring performances are established. The results indicate that with moderate secondary to primary mass flow rate ratios, ranging around 5 %, it is possible to achieve pertinent vector side forces. It is also revealed that injector positioning and geometry have a strong effect on the shock vector control system and nozzle performances.
Complete list of metadata

https://hal.archives-ouvertes.fr/hal-01176489
Contributor : Frédéric Davesne Connect in order to contact the contributor
Submitted on : Wednesday, July 15, 2015 - 2:51:38 PM
Last modification on : Wednesday, October 27, 2021 - 11:26:44 AM

Identifiers

Collections

Citation

Vladeta Zmijanović, Viviana Lago, Mohamed Sellam,, Amer Chpoun. Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection. Shock Waves, Springer Verlag, 2014, 24 (1), pp.97--111. ⟨10.1007/s00193-013-0479-y⟩. ⟨hal-01176489⟩

Share

Metrics

Les métriques sont temporairement indisponibles