TY - GEN
T1 - Spanwise Wavenumber Perturbation on a Splitter Plate in a Rectangular Supersonic Nozzle
AU - Gist, Emma D.
AU - Kelly, Seth W.
AU - Chatterjee, Rishov
AU - Doshi, Parshwanath S.
AU - Glauser, Mark N.
AU - Gaitonde, Datta V.
N1 - Funding Information:
This study was provided funding by the Air Force Office of Scientific Research (AFOSR) grant number FA9550-19-1-0081, Dr. Gregg Abate, program manager. The authors would like to thank Dr. Jacques Lewalle, whose findings served as inspiration of this study and the Skytop Turbulence Laboratory team for their hard work and dedication to this project. We would also like to thank the High-Fidelity Computational Multi-Physics Laboratory from The Ohio State University for providing simulations for comparison.
Funding Information:
This study was provided funding by the Air Force Office of Scientific Research (AFOSR) grant number FA955019-1-0081, Dr. Gregg Abate, program manager. The authors would like to thank Dr. Jacques Lewalle, whose findings served as inspiration of this study and the Skytop Turbulence Laboratory team for their hard work and dedication to this project. We would also like to thank the High-Fidelity Computational Multi-Physics Laboratory from The Ohio State University for providing simulations for comparison.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Passive control is applied to a modern adaptive engine design and its effectiveness compared to an unaltered configuration. The adaptive engine is represented by a supersonic multi-stream rectangular jet nozzle comprised of a core stream (M = 1.6) and bypass (M = 1.0) who merge behind a splitter plate and exit through a SERN onto an aft-deck plate. LES performed at The Ohio State University have identified the splitter plate trailing edge (SPTE) as a highly sensitive region for altering the overall nature of the flow. It has been shown that the shedding frequency initiated at the SPTE acts as a dominating tone throughout the flowfield. As a means for passive control, and an attempt to mitigate this tone, a spanwise perturbation has been introduced to the SPTE and implemented experimentally at Syracuse University. Farfield acoustics and near-field pressure measurements have confirmed the diminishment of the dominant tone for the wavy SPTE. To simulate the nozzle being integrated into an existing airframe, tests are conducted with three different aft deck geometries: a nominal length deck, half nominal, and no deck. PIV of the nominal configuration showed a slight change in the deflection angle of the jet plume. The differences for the half and no deck cases were less significant. These results along with future analyses will be used as a point of comparison between the two splitter plate configurations and act as means to validify the accuracy of the LES.
AB - Passive control is applied to a modern adaptive engine design and its effectiveness compared to an unaltered configuration. The adaptive engine is represented by a supersonic multi-stream rectangular jet nozzle comprised of a core stream (M = 1.6) and bypass (M = 1.0) who merge behind a splitter plate and exit through a SERN onto an aft-deck plate. LES performed at The Ohio State University have identified the splitter plate trailing edge (SPTE) as a highly sensitive region for altering the overall nature of the flow. It has been shown that the shedding frequency initiated at the SPTE acts as a dominating tone throughout the flowfield. As a means for passive control, and an attempt to mitigate this tone, a spanwise perturbation has been introduced to the SPTE and implemented experimentally at Syracuse University. Farfield acoustics and near-field pressure measurements have confirmed the diminishment of the dominant tone for the wavy SPTE. To simulate the nozzle being integrated into an existing airframe, tests are conducted with three different aft deck geometries: a nominal length deck, half nominal, and no deck. PIV of the nominal configuration showed a slight change in the deflection angle of the jet plume. The differences for the half and no deck cases were less significant. These results along with future analyses will be used as a point of comparison between the two splitter plate configurations and act as means to validify the accuracy of the LES.
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U2 - 10.2514/6.2022-0052
DO - 10.2514/6.2022-0052
M3 - Conference contribution
AN - SCOPUS:85122671372
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
SP - 1
EP - 11
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -