Measurements and computations of second-mode instability waves in three hypersonic wind tunnels.
- Aerospace Testing Alliance, Silver Spring, MD
- Air Force Research Laboratory, Wright-Patterson AFB, OH
- NASA Langley Research Center, Hampton, VA
- Purdue University, West Lafayette, IN
High-frequency pressure-fluctuation measurements were made in AEDC Tunnel 9 at Mach 10 and the NASA Langley 15-Inch Mach 6 and 31-Inch Mach 10 tunnels. Measurements were made on a 7{sup o}-half-angle cone model. Pitot measurements of freestream pressure fluctuations were also made in Tunnel 9 and the Langley Mach-6 tunnel. For the first time, second-mode waves were measured in all of these tunnels, using 1-MHz-response pressure sensors. In Tunnel 9, second-mode waves could be seen in power spectra computed from records as short as 80 {micro}s. The second-mode wave amplitudes were observed to saturate and then begin to decrease in the Langley tunnels, indicating wave breakdown. Breakdown was estimated to occur near N {approx} 5 in the Langley Mach-10 tunnel. The unit-Reynolds-number variations in the data from Tunnel 9 were too large to see the same processes.
- Research Organization:
- Sandia National Laboratories (SNL), Albuquerque, NM, and Livermore, CA (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- AC04-94AL85000
- OSTI ID:
- 1020373
- Report Number(s):
- SAND2010-4020C; TRN: US201116%%298
- Resource Relation:
- Conference: Proposed for presentation at the 40th AIAA Fluid Dynamics Conference held June 28-July 1, 2010 in Chicago, IL.
- Country of Publication:
- United States
- Language:
- English
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