Dynamics of a 3-D Inlet/Isolator Measured with Fast Pressure-Sensitive Paint

Authors

• Andrew N. Bustard, University of Notre Dame
• Mark E. Noftz, Purdue University
• Mitsugu Hasegawa, University of Notre Dame
• Hirotaka Sakaue, University of Notre Dame
• Joseph S. Jewell, Purdue University
• Nicholas J. Bisek, Air Force Research Laboratory
• Thomas J. Juliano, University of Notre Dame

Submitting Campus

Daytona Beach

Department

Aerospace Engineering

Document Type

Article

Publication/Presentation Date

2024

Abstract/Description

Fast pressure-sensitive paint (PSP) was applied to an inlet/isolator designed using the Osculating Internal Waverider Inlet with Parallel Streamlines (OIWPS) method. The dorsal isolator surface pressure was measured using anodized-aluminum PSP through transparent cast acrylic that makes up the ventral portion of the isolator. Temperature-sensitive paint was utilized to correct for the PSP’s temperature sensitivity. The model was tested under Mach 5.7 flow at Re = 8.5 ×106 /m and 10.2 ×106 /m in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel (ANDLM6QT) under conventional noise conditions. Flow phenomena, such as shocks originating in the inlet and flow separation at the throat, were visualized with high spatial resolution. The dynamics measured by the PSP and pressure transducers matched well where the spectral signal-to-noise ratio was above unity. Power spectral densities showed significant frequency content at ≈1 kHz in the shockwave/boundary-layer interaction (SWBLI) regions. Coherence analysis showed a linear relationship between the unsteady pressures at locations underneath different SWBLI in the isolator, with the exception of the Busemann throat shock. Temporal correlation of shock positions indicated that disturbances propagated downstream at 114% of the core-flow velocity; however, improved calculations of the core-flow velocity are needed to refine this assessment. The surface pressure fields at Re = 8.5 ×106 /m and 10.2 ×106 /m were quantitatively very similar, and the results in the ANDLM6QT were qualitatively similar to previous studies in the Boeing/AFOSR Mach-6 Quiet Tunnel under noisy flow.

Publication Title

Experiments in Fluids

DOI

https://doi.org/10.1007/s00348-024-03836-7

Article Number

106

Publisher

Springer Nature Link

Grant or Award Name

U.S. Air Force Research Laboratory Award number FA8650-20-2-2405

Additional Information

Dr. Bustard was not affiliated with Embry-Riddle Aeronautical University at the time this paper was published.

Scholarly Commons Citation

Bustard, A.N., Noftz, M.E., Hasegawa, M. et al. Dynamics of a 3-D inlet/isolator measured with fast pressure-sensitive paint. Exp Fluids 65, 106 (2024). https://doi.org/10.1007/s00348-024-03836-7