Flow characterization of a supersonic and hypersonic arc-heated wind tunnel

Erik M. Hoberg, Christopher Huffman, Nicholas Sanchez-Plesha, Carson L. Running, Nozomu Kato, Seong Kyun Im, Thomas J. Juliano

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Citations (Scopus)


The University of Notre Dame arc-heated hypersonic wind tunnel, ACT-1, was built in 2015 to study combustion in the supersonic and hypersonic flow regimes. Since its construction, little has been done to assess its flow quality. A pitot-rake survey has now been conducted at multiple axial and radial stations for arc-off (stagnation temperature ≈ 295 K) conditions. For a stagnation pressure of 380 kPa, the average measured Mach number at the nozzle exit plane was 4.7 and 6.3 for the Mach-4.5 and-6 nozzles, respectively. The flow fields of both nozzles exhibited slight angularity and asymmetry. Kulite pressure transducers measured the spectral content of noise in the flow for frequencies up to 127.5 kHz. The root-mean-squared of the pitot pressure was found to be 2.2–2.4% and 0.5–2.2% of the mean pitot pressure for the Mach-4.5 and-6 nozzles, respectively. Measurements with a static pressure probe indicated that condensation prematurely shortened the axial length of the uniform flow region for the Mach-6 nozzle. This effect was larger at lower stagnation temperatures. No condensation was observed for the Mach-4.5 nozzle.

Original languageEnglish
Title of host publicationAIAA Aviation 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Number of pages19
ISBN (Print)9781624105890
Publication statusPublished - 2019
Externally publishedYes
EventAIAA Aviation 2019 Forum - Dallas, United States
Duration: 2019 Jun 172019 Jun 21

Publication series

NameAIAA Aviation 2019 Forum


ConferenceAIAA Aviation 2019 Forum
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Computer Science Applications
  • Electrical and Electronic Engineering
  • Aerospace Engineering


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