TY - JOUR
T1 - Experimental Study of Aeroelastic Response and Performance of a Hypersonic Intake Ramp
AU - Bhattrai, Sudip
AU - McQuellin, Liam P.
AU - Currao, Gaetano M.D.
AU - Neely, Andrew J.
AU - Buttsworth, David R.
N1 - Funding Information:
This material is based upon work supported by the U.S. Air Force Office of Scientific Research under award number FA2386-19-1-4027. Numerical resources were provided by the National Computational Infrastructure, under the National Computational Merit Allocation Scheme, which is supported by the Australian Government. The authors would like to thank Byrenn Birch, Lachlan Noller, and Brian Lenski for their support during the experiments at the tunnel at University of Southern Queensland (TUSQ) hypersonic test facility and to Murali Krishna Talluru for providing meticulous suggestions and feedback on this manuscript. Any opinion, finding, and conclusions or recommendations expressed in this material are those of the authors and do not necessarily reflect the views of the U.S. Air Force.
Publisher Copyright:
© 2021 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
PY - 2022
Y1 - 2022
N2 - The response and performance of an aeroelastic hypersonic intake was studied experimentally using fundamental geometry and structural boundary conditions. The experiments were conducted in a hypersonic wind tunnel at a Mach 5.85 condition. The most relevant deforming component was the compression ramp, which was treated as a cantilever surface to emulate the global deformation of the intake. Flowfield measurements were performed using pressure transducers, pressure-sensitive paints, and schlieren flow visualization. The dynamic structural response was measured using digital image correlation as well as feature tracking from the schlieren videos. A point measurement of total pressure in the isolator was taken using a pitot tube to quantify the effects of intake ramp deformation on the intake performance. The loss of total pressure in the isolator was found to correlate directly with the intake ramp deformation, with a direct transient correlation between the peak loss in total pressure recovery and the peak ramp deformation. While undergoing aeroelastic deformation, the total pressure recovery of the cantilever compliant ramp decreased by up to 20% from the baseline values. The analysis showed a strong coupling, along with hysteresis in dynamic response, between the intake structural deformation and the shock-wave/boundary-layer flowfield in the isolator.
AB - The response and performance of an aeroelastic hypersonic intake was studied experimentally using fundamental geometry and structural boundary conditions. The experiments were conducted in a hypersonic wind tunnel at a Mach 5.85 condition. The most relevant deforming component was the compression ramp, which was treated as a cantilever surface to emulate the global deformation of the intake. Flowfield measurements were performed using pressure transducers, pressure-sensitive paints, and schlieren flow visualization. The dynamic structural response was measured using digital image correlation as well as feature tracking from the schlieren videos. A point measurement of total pressure in the isolator was taken using a pitot tube to quantify the effects of intake ramp deformation on the intake performance. The loss of total pressure in the isolator was found to correlate directly with the intake ramp deformation, with a direct transient correlation between the peak loss in total pressure recovery and the peak ramp deformation. While undergoing aeroelastic deformation, the total pressure recovery of the cantilever compliant ramp decreased by up to 20% from the baseline values. The analysis showed a strong coupling, along with hysteresis in dynamic response, between the intake structural deformation and the shock-wave/boundary-layer flowfield in the isolator.
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U2 - 10.2514/1.B38348
DO - 10.2514/1.B38348
M3 - Article
AN - SCOPUS:85122849877
VL - 38
SP - 157
EP - 170
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
SN - 0748-4658
IS - 1
ER -