TY - GEN
T1 - Numerical Investigation of Droplet Aerobreakup and Impingement Experiments at Mach 5
AU - Viqueira-Moreira, Manuel
AU - Dworzanczyk, A.
AU - Parziale, N. J.
AU - Brehm, Christoph
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - Droplet simulations with and without phase change have been performed to further our understanding of the relevant physics involved in aerobreakup and impingement of water droplets at hypersonic flow speeds and large Weber numbers. The numerical simulations are conducted closely following light-gas gun experiments performed at the Southwest Research Institute. A robust higher-order WENO-based multiphase numerical method is used with the assumption of thermo-chemical equilibrium (infinitely fast relaxation) to enable simulations of the post-impingement phase. Adaptive mesh refinement allows for computationally efficient tracking of important flow features such as liquid/vapor/gas interfaces, shocks and wakes. The target geometry is modeled using an immersed boundary method. This paper aims to investigate the dominant physical mechanisms by simulating the problem considering different modeling fidelity such as with and without viscous effects and/or with and without phase change. This approach allows to explore how the droplet breakup is affected by these associated physical mechanisms. It was found that the vapor layer plays an important role in the droplet aerobreakup on the front face of the droplet as well as for the wake dynamics. The final droplet impingement phase could be robustly simulated with the current approach and, while not perfectly matching the experiment, the complexity of the relevant flow physics could still be investigated by comparing the simulation results with the experimental data.
AB - Droplet simulations with and without phase change have been performed to further our understanding of the relevant physics involved in aerobreakup and impingement of water droplets at hypersonic flow speeds and large Weber numbers. The numerical simulations are conducted closely following light-gas gun experiments performed at the Southwest Research Institute. A robust higher-order WENO-based multiphase numerical method is used with the assumption of thermo-chemical equilibrium (infinitely fast relaxation) to enable simulations of the post-impingement phase. Adaptive mesh refinement allows for computationally efficient tracking of important flow features such as liquid/vapor/gas interfaces, shocks and wakes. The target geometry is modeled using an immersed boundary method. This paper aims to investigate the dominant physical mechanisms by simulating the problem considering different modeling fidelity such as with and without viscous effects and/or with and without phase change. This approach allows to explore how the droplet breakup is affected by these associated physical mechanisms. It was found that the vapor layer plays an important role in the droplet aerobreakup on the front face of the droplet as well as for the wake dynamics. The final droplet impingement phase could be robustly simulated with the current approach and, while not perfectly matching the experiment, the complexity of the relevant flow physics could still be investigated by comparing the simulation results with the experimental data.
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U2 - 10.2514/6.2023-4251
DO - 10.2514/6.2023-4251
M3 - Conference contribution
AN - SCOPUS:85195588315
SN - 9781624107047
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
Y2 - 12 June 2023 through 16 June 2023
ER -