Supersonic Axis-symmetric Mixed-Compression Inlet Using Zero-Net-Mass-Flux CoFlow Jet Flow Control

Zhijin Lei, Yan Ren, Gecheng Zha

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper numerically studies a new zero-net-mass-flux (ZNMF) coflow jet (CFJ) active control to increase the unstart margin and efficiency of axis-symmetric mixed-compression supersonic inlets without dumping the bleed flow. The simulation is done by using the in-house CFD code FASIP that solves 3D Reynolds-averaged Navier-Stokes (RANS) equations with 3rd order MUSCL scheme for shock capturing, 2nd order central differencing for the viscous terms, and the Spalart-Allmaras model for turbulence. The CFD simulation is validated with the tested NASA VDC Inlet at Mach 2.0 for its critical condition at angle of attack (AoA) of 0 . Good agreement between the CFD simulation and experiment at critical condition is achieved for the streamwise surface pressure distribution, total pressure profiles at different streamwise locations, total pressure recovery, and fan face distortion. The CFD simulation indicates that the baseline inlet remains started at AoA of 1.2 and unstarts at AoA of 1.6 . A CFJ inlet concept is studied to improve the baseline inlet performance. The CFJ flow control withdraws the mass flow of boundary layer at the same throat position as conventional bleed, but injects the mass flow back to the inlet diffuser area downstream. It thus has a constant mass flow from the supersonic inlet entrance to the engine entrance similar to subsonic inlets. The mechanism of CFJ active flow control to stabilize axis-symmetric inlet is two-fold: i) The suction in the throat bleed region has the same effect as conventional bleed to remove the thick boundary layer and increase flow passing capacity. ii) The downstream injection further energizes the boundary layer in the diffuser region to reduce flow blockage, increases flow passing capacity, and increases inlet stability against unstart. With a 5% less bleed flow than that of the baseline inlet, the CFJ inlet is able to stabilize the inlet at AoA of 2 with higher inlet stability and total pressure recovery, while keeping the constant mass flow in the inlet. More numerical studies to investigate the working mechanism of CFJ inlets are in progress.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum 2022
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106316
DOIs
StatePublished - 2022
Externally publishedYes
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 - San Diego, United States
Duration: Jan 3 2022Jan 7 2022

Publication series

NameAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Country/TerritoryUnited States
CitySan Diego
Period1/3/221/7/22

ASJC Scopus subject areas

  • Aerospace Engineering

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