TY - GEN
T1 - Isolator shock dynamics of mass injection-induced unstart in a circular model scramjet
AU - Baccarella, Damiano
AU - Liu, Qili
AU - McGann, Brendan
AU - Lee, Tonghun
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - The shock dynamics in the isolator of a free-jet model scramjet is investigated during unstart at low enthalpy conditions. Mass injection is used to choke the combustor flow and cause unstart by simulating the blockage effect of combustion heat release. The model scramjet used has a constant area circular cross section and optically accessible isolator and combustor. A detailed characterization of the unstart process was provided by wall pressure measurements and high-speed (10 kHz) CO2 Rayleigh scattering imaging. In response to the backpressure rise induced by mass injection, the flow in the isolator separates, forming a shock-train. The flow in the combustor stays supersonic until choking occurs near the exit. Once the flow is choked, a pseudo-shock propagates upstream and reaches the injectors location, where it starts interacting with the isolator shock-train. Under particularly severe blockage conditions the shock system ultimately disgorges from the inlet causing unstart.
AB - The shock dynamics in the isolator of a free-jet model scramjet is investigated during unstart at low enthalpy conditions. Mass injection is used to choke the combustor flow and cause unstart by simulating the blockage effect of combustion heat release. The model scramjet used has a constant area circular cross section and optically accessible isolator and combustor. A detailed characterization of the unstart process was provided by wall pressure measurements and high-speed (10 kHz) CO2 Rayleigh scattering imaging. In response to the backpressure rise induced by mass injection, the flow in the isolator separates, forming a shock-train. The flow in the combustor stays supersonic until choking occurs near the exit. Once the flow is choked, a pseudo-shock propagates upstream and reaches the injectors location, where it starts interacting with the isolator shock-train. Under particularly severe blockage conditions the shock system ultimately disgorges from the inlet causing unstart.
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M3 - Conference contribution
AN - SCOPUS:85087869472
SN - 9781624106002
T3 - 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2020
BT - 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2020
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2020
Y2 - 10 March 2020 through 12 March 2020
ER -