Abstract
Fuel–air mixing remains a critical challenge in the development of high-speed air-breathing propulsion due to the extremely short residence times in supersonic combustors. Experimental studies are essential to investigate the underlying mixing mechanisms, but they require injection systems that can deliver repeatable and controlled flow conditions. In this work, we present the design of a modular strut-type injection platform developed for the Missouri S&T Supersonic Wind Tunnel. In its initial configuration, the platform features a planar trailing-edge slit to generate a two-dimensional jet and includes interchangeable trailing-edge modules to support a wide range of geometries and flow-control strategies. Designed with aerodynamic performance, structural integrity, thermal constraints, and diagnostic access in mind, this platform enables systematic, high-fidelity studies of supersonic mixing.
Recommended Citation
C. Bell and D. Viganò, "Versatile Injector Platform: A Modular Design for Supersonic Flow Research," AIAA Aviation Forum and Ascend 2025, American Institute of Aeronautics and Astronautics, Jan 2025.
The definitive version is available at https://doi.org/10.2514/6.2025-3050
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
Keywords and Phrases
Aerodynamic Interference; Aerodynamic Performance; Fuel Injection; High Speed Air Breathing Propulsion; Internal Pressure; Structural Integrity; Supersonic Combustor; Supersonic Wind Tunnels; Trailing Edges; Two Dimensional Flow
International Standard Book Number (ISBN)
978-162410738-2
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2025 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2025
