Preliminary Design of a Mach 6 Nozzle and Direct Connect Test System
Location
Havener Center, Miner Lounge / Wiese Atrium, 9:30am-11:30am
Start Date
4-1-2026 9:30 AM
End Date
4-1-2026 11:30 AM
Presentation Date
April 1, 2026; 9:30am-11:30am
Description
Advancing wind tunnel capability to Mach 6 requires careful design of the nozzle to achieve the desired flow conditions while maintaining stability and uniformity in the test section. This work presents a preliminary design study of a supersonic nozzle for Missouri S&T’s proposed high-speed wind tunnel facility. Key considerations include nozzle contouring, area ratio selection, and expansion characteristics necessary to produce uniform Mach 6 flow while minimizing boundary layer effects and flow nonuniformities. The study evaluates design methodologies based on established compressible flow theory and reviews existing high-speed nozzle configurations to inform geometry selection. Scaling analyses are conducted to estimate geometric parameters and assess sensitivity to operating conditions. Preliminary nozzle profiles are generated and compared with respect to flow quality and feasibility of fabrication. Results provide initial design guidelines and identify critical factors influencing performance, establishing a foundation for future detailed nozzle development and optimization.
Biography
I am a senior in Aerospace Engineering from St. Louis, doing undergraduate research for Dr. Viganó in the Aerodynamics Research Laboratory. I am doing preliminary design work on the nozzle of a Mach 6 wind tunnel for the lab, as well as on a nozzle and test system for a direct connect propulsion experimentation tunnel. I am also a part of the Miner Aviation Student Design Team, of which I have been involved in all four years of college. I have held the positions of CFO, Integration and Manufacturing (Structural Engineer) Team Lead, and am currently the team's CEO. After graduation, I will be working fulltime in Boeing's Phantom Works division as a loads and dynamics engineer, while also pursuing my Master's in Aerospace Engineering online through Missouri S&T.
Meeting Name
2026 - Miners Solving for Tomorrow Research Conference
Department(s)
Mechanical and Aerospace Engineering
Document Type
Poster
Document Version
Final Version
File Type
event
Language(s)
English
Rights
© 2026 The Authors, All rights reserved
Preliminary Design of a Mach 6 Nozzle and Direct Connect Test System
Havener Center, Miner Lounge / Wiese Atrium, 9:30am-11:30am
Advancing wind tunnel capability to Mach 6 requires careful design of the nozzle to achieve the desired flow conditions while maintaining stability and uniformity in the test section. This work presents a preliminary design study of a supersonic nozzle for Missouri S&T’s proposed high-speed wind tunnel facility. Key considerations include nozzle contouring, area ratio selection, and expansion characteristics necessary to produce uniform Mach 6 flow while minimizing boundary layer effects and flow nonuniformities. The study evaluates design methodologies based on established compressible flow theory and reviews existing high-speed nozzle configurations to inform geometry selection. Scaling analyses are conducted to estimate geometric parameters and assess sensitivity to operating conditions. Preliminary nozzle profiles are generated and compared with respect to flow quality and feasibility of fabrication. Results provide initial design guidelines and identify critical factors influencing performance, establishing a foundation for future detailed nozzle development and optimization.
Comments
Advisor: Davide Vigano, dvigano@mst.edu