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Surface Properties of Double-Fin Generated Shock-Wave/Boundary-Layer Interactions

Journal Article · · AIAA Journal
DOI:https://doi.org/10.2514/1.j062886· OSTI ID:2475596
 [1];  [1];  [1];  [1];  [2]
  1. Florida State Univ., Tallahassee, FL (United States)
  2. Los Alamos National Laboratory (LANL), Los Alamos, NM (United States)
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Shock-Wave/Boundary-Layer Interaction (SBLI) is ubiquitous in high-speed air vehicles. SBLI surface flowfield properties of crossing shocks induced by symmetric Double-Fins (DFs) at fin angles of 8° and 10° at Mach 2 are experimentally investigated; a 10° Single-Fin (SF) is also explored as a comparison. Surface visualization is used to capture distinct flowfield structures such as separation and upstream influence. Steady and unsteady Pressure-Sensitive Paints (PSPs) are used to obtain global surface pressure fields. Characteristics of DF-SBLI surface topology are discussed by comparing the corresponding SF-SBLI. Here, the effect of fin angle on DF-SBLI is characterized, and unsteady dynamics of the pressure field are examined. Spectral Proper Orthogonal Decomposition (SPOD) is performed on unsteady PSP, and traveling surface pressure waves and their frequency-dependent behavior are discussed. Dispersion relation of surface pressure waves is revealed by performing two-dimensional space–time Fourier transform on unsteady PSP, and the results are compared with the phase velocity distributions obtained from SPOD. Accompanying group velocity behavior is examined for distinct SBLI regions wherein wave propagation is found dependent on its frequency. Steady surface pressures along the centerline are compared with previous experimental data. Fin-tip spacing is found to be an essential parameter for scaling of upstream influence length.

Research Organization:
Los Alamos National Laboratory (LANL), Los Alamos, NM (United States)
Sponsoring Organization:
USDOE National Nuclear Security Administration (NNSA); USDOD; US Air Force Office of Scientific Research (AFOSR)
Grant/Contract Number:
89233218CNA000001
OSTI ID:
2475596
Report Number(s):
LA-UR--23-20548
Journal Information:
AIAA Journal, Journal Name: AIAA Journal Journal Issue: 12 Vol. 61; ISSN 0001-1452
Publisher:
AIAACopyright Statement
Country of Publication:
United States
Language:
English

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Related Subjects

33 ADVANCED PROPULSION SYSTEMS
Crossing Shocks
Dispersive Waves
Double-fin
Experimental Fluid Dynamics
High-Speed Inlets
Hypersonic Air-Breathing Propulsion
Pressure-Sensitive Paint (PSP)
Sharp Fin Aerodynamics
Shock-Wave/Boundary-Layer Interaction (SBLI)
Spectral Proper Orthogonal Decomposition (SPOD)
Supersonic Flow
Supersonic Wind Tunnel