Design of a high-speed intake distortion simulator for propulsion integration research

Abstract

High levels of inlet flow distortion can be a critical aspect in supersonic air induction systems due to the complex spatial nature and notable temporal unsteadiness. This can affect the operability and performance of the propulsion system. Simulation of the intake shock system in a relatively less expensive, lower technology readiness level experimental facility can be an important element to mitigate a significant part of the risk that industrial and certification testing carries. The work described in this paper is part of a programme that aims to develop such a distortion simulation test rig where the capability of advanced nonintrusive measurement techniques would be applied in propulsion integration research. The paper describes the concept, preliminary design and sizing of the working section of the rig, the exhaust system design and the integration of the test model. A brief summary of the rig architecture is provided along with details of the high-pressure system that drives the supersonic flow. The work indicates that careful design of the working section is required to ensure sufficient operating range and representative aerodynamics of the test model. It is also shown that the working section wall interference on the test model is tightly linked with the type and size of the aircraft intake to be tested. Ways to mitigate this interference are herein explored. I.Nomenclature ACIntake capture area AH Working section cross-sectional area A0 Area of stream tube entering the inlet Amax Maximum inlet projected area, A* Nozzle throat area Cp Static pressure coefficient H Working section height Ht Intake throat height h Diverter height

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

“…The process of designing this small-scale facility was recently presented by Migliorini et al [233], with a particular focus on the working test section design to ensure an adequate operational range and representative aerodynamic conditions for the test model. The study provides a detailed account of the ongoing work, encompassing the conceptualization, initial design, and sizing of the working section of the test rig, as well as the design of the exhaust system and the integration of the test model.…”