Shedding Intermittency in a Shock Wave-Laminar Boundary Layer Interaction

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Adaptation of the Transpiration Method to Simulate the Fluid–Structure Interaction Phenomena for a Flexible Overexpanded Rocket Nozzle

International audienceThe aim of this paper is to present a new aeroelastic stability model taking into account the viscous effects for a supersonic nozzle flow in overexpanded regimes. This model is inspired from the Pekkari model which was developed initially for perfect fluid flow. The new model called the “modified Pekkari model” (MPM) considers a more realistic wall pressure profile for the case of a free shock separation (FSS) inside the supersonic nozzle using the free interaction theory of Chapman. The main results are presented in a comparative manner using existing models (Pekkari model and its extended version) and the modified Pekkari model developed in this work

A New Modified Pekkari Model to Analyse the Aeroelastic Stability Behaviour for a Flexible Over-Expanded Roket Nozzle

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Secondary Injectant Gas Thermodynamic Properties Effects on Fluidic Thrust Vectoring Performances of a Supersonic Nozzle

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New Modified Pekkari Model to Analyse the Aeroelastic Stability Behaviour for a Flexible Overexpanded Rocket Nozzle

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Shock Waves in Hypersonic Rarefied Flows

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Etude de Léffet Thermique Sur Les Performances Aérodynamiques Des Microdrones (MAV)

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Adaptation of the Transpiration Method to Simulate the Fluid–Structure Interaction Phenomena for a Flexible Overexpanded Rocket Nozzle

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