TY - GEN
T1 - On Linear Stability of Compression Corner Flows Obtained by Kinetic Theory
AU - Karpuzcu, Irmak T.
AU - Levin, Deborah A.
AU - Cerulus, Nicolas
AU - Theofilis, Vassilis
N1 - The research conducted in this paper is supported by the Office of Naval Research under Grant No. N000141202195 titled “Multi-scale modelling of unsteady shock-boundary layer hypersonic flow instabilities,” with Dr. Eric Marineau as the Program Officer. This research is also supported by NSF XSEDE’s Frontera supercomputer with the project number CTS21001.
PY - 2022
Y1 - 2022
N2 - Two-dimensional supersonic flow over several compression corners are computed by Direct Simulation Monte Carlo (DSMC) and their linear global stability analysed by solution of the compressible BiGlobal eigenvalue problem on generalised coordinates. The base flow features a large separation bubble, while time resolved data showed that the flow reached a steady state at the parameters examined. The maximum recirculation, calculated by reference to the free stream velocity, is found to be around 10% for all cases. Linear stability analysis performed confirms this conjecture, yielding a globally stable solution for a wide range of spanwise wavenumbers. The two-dimensional (spanwise wavenumber β = 0) limit is found to be the least stable, an increase of β leading to more stable spectra while retaining the same leading stationary mode. Higher scaled ramp angles, leading to substantially higher recirculation levels, are currently being analyzed.
AB - Two-dimensional supersonic flow over several compression corners are computed by Direct Simulation Monte Carlo (DSMC) and their linear global stability analysed by solution of the compressible BiGlobal eigenvalue problem on generalised coordinates. The base flow features a large separation bubble, while time resolved data showed that the flow reached a steady state at the parameters examined. The maximum recirculation, calculated by reference to the free stream velocity, is found to be around 10% for all cases. Linear stability analysis performed confirms this conjecture, yielding a globally stable solution for a wide range of spanwise wavenumbers. The two-dimensional (spanwise wavenumber β = 0) limit is found to be the least stable, an increase of β leading to more stable spectra while retaining the same leading stationary mode. Higher scaled ramp angles, leading to substantially higher recirculation levels, are currently being analyzed.
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U2 - 10.2514/6.2022-4102
DO - 10.2514/6.2022-4102
M3 - Conference contribution
AN - SCOPUS:85135084344
SN - 9781624106354
T3 - AIAA AVIATION 2022 Forum
BT - AIAA AVIATION 2022 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2022 Forum
Y2 - 27 June 2022 through 1 July 2022
ER -