DESIGN, CONSTRUCTION, AND FLOW SIMULATION OF A MACH 5+ HYPERSONIC WIND TUNNEL
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Authors
Deer, Christopher E.
Subjects
hypersonic
wind tunnel
modeling
simulation
compressible flow
computational fluid dynamics
nozzle
hypersonic wind tunnel
blowdown wind tunnel
Mach 5
wind tunnel
modeling
simulation
compressible flow
computational fluid dynamics
nozzle
hypersonic wind tunnel
blowdown wind tunnel
Mach 5
Advisors
Hobson, Garth V.
Smith, Walter C.
Date of Issue
2024-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
With substantial interest in the development of hypersonic weapon systems and reentry vehicles, wind tunnels are a crucial asset when validating computer simulations and iterating designs in a cost-effective manner. The significance of a wind tunnel is shown in this paper by testing a reentry vehicle at hypersonic speeds, simulating the body re-entering atmosphere. The wind tunnel could be used to validate computer simulations that determine the shock behavior and where significant aerodynamic pressures occur. This thesis focuses on the design and construction of a Mach 5+ hypersonic wind tunnel in Naval Postgraduate School’s Gas Dynamics Lab. The paper first covers the wind tunnel’s test section design process and predicts metrics using existing wind tunnel components through computational fluid dynamic simulations. The structural strength of the design is also evaluated using a finite element analysis simulation. The design of each test section component is also detailed, along with the tunnel construction process. The process for coding a PID controller for the air supply valve is described, along with the instructions for operation. The process of validating a prototype reentry vehicle’s computational fluid dynamic simulation using the current Mach 4.0 is then discussed. Finally, the project status is detailed with future work that can continue Naval Postgraduate School’s efforts to have a Mach 5+ hypersonic wind tunnel.
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Thesis
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Distribution Statement
Distribution Statement A. Approved for public release: Distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.