Project Details
[Return to Previous Page]Subscale Supersonic Wind Tunnel Facility
Company: The Johns Hopkins University Applied Physics Laboratory
Major(s):
Primary: ME
Non-Disclosure Agreement: NO
Intellectual Property: NO
Concept: Ground testing is essential to evaluate the design and performance of hypersonic vehicles. These vehicles are subjected to harsh environmental conditions in flight (extreme temperatures, pressures, etc.), which must be replicated in material- and component-level tests. Tests are typically performed in shock tunnel and arcjet facilities that are expensive to operate. However, a large test section and high-enthalpy flow are not required for material-level coupon testing. Component Description: The test bed may be used by The Johns Hopkins University Applied Physics Laboratory to inform on-site wind tunnel design for material-level thermal testing. The prototype wind tunnel shall consist of a reservoir, converging-diverging nozzle, test section, and diffuser. It shall be capable of operating at supersonic speeds. Technical Need: Design and prototype a wind tunnel capable of providing supersonic flow over a small (one square inch) material sample. The exit diameter of the nozzle should be between 3 and 6 inches. The wind tunnel should run using compressed air and/or a vacuum pump. The team may consider 3D printed manufacturing methods for their design. Challenges: The design of a supersonic wind tunnel requires careful analysis to overcome key issues such as proper tunnel startup, sufficient test time, steady flow conditions, and uniform coreflow.