Initial Shakedown Testing of the Stevens Shock Tunnel

D. Shekhtman, A. Hameed, B. A. Segall, A. R. Dworzanczyk, N. J. Parziale

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

6 Scopus citations

Abstract

The Stevens Shock Tunnel is designed to replicate hypersonic, Mach 6 flow conditions. The tunnel produces a core flow of 0.3 m in the test section and a test time of at least 4 ms. This paper describes the tunnel’s operation and flow characterization for a range of run conditions: Mach 5.8-6.0, enthalpy 1.5 MJ/Kg, and unit Reynolds number 0.35-8.1 × 106 1/m (with a potentially lower limit available). This paper also describes the use of a nozzle centerbody flow terminator and debris blocker and tunnel cleaning to remove residual debris from a previous experiment. Reservoir, static, and Pitot pressure measurements are presented for a range of run conditions and compared to nozzle flow calculations.

Original languageEnglish
Title of host publicationAIAA SciTech Forum 2022
DOIs
StatePublished - 2022
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 - San Diego, United States
Duration: 3 Jan 20227 Jan 2022

Publication series

NameAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Country/TerritoryUnited States
CitySan Diego
Period3/01/227/01/22

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