Abstract
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 language | English |
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Title of host publication | AIAA Aviation 2019 Forum |
Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
Pages | 1-19 |
Number of pages | 19 |
ISBN (Print) | 9781624105890 |
Publication status | Published - 2019 |
Externally published | Yes |
Event | AIAA Aviation 2019 Forum - Dallas, United States Duration: 2019 Jun 17 → 2019 Jun 21 |
Publication series
Name | AIAA Aviation 2019 Forum |
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Conference
Conference | AIAA Aviation 2019 Forum |
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Country/Territory | United States |
City | Dallas |
Period | 19/6/17 → 19/6/21 |
Bibliographical note
Publisher Copyright:© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
ASJC Scopus subject areas
- Computer Science Applications
- Electrical and Electronic Engineering
- Aerospace Engineering