Femtosecond Coherent Anti-Stokes Raman Spectroscopy in a Cold-Flow Hypersonic Wind Tunnel for Simultaneous Pressure and Temperature Measurements.
Abstract not provided.
Richardson, Daniel↗
Engineering topics
Kearney, Sean
Publications and source records attributed to Kearney, Sean.
Demonstration of a Burst-Mode-Pumped Noncolinear Optical Parametric Oscillator (NOPO) for Broadband CARS Diagnostics in Gases.
Abstract not provided.
Jans, Elijah↗
Multi-Color Pyrometry of High-speed Ejecta from Pyrotechnic Igniters.
Abstract not provided.
Halls, Benjamin↗
Burst-mode coherent anti-Stokes Raman scattering thermometry in the Sandia free-piston shock tube.
Abstract not provided.
Kearney, Sean↗
Toward Snapshot Cross-Correlation Doppler Global Velocimetry for High-Speed Flows.
Abstract not provided.
Saltzman, Ashley↗
Toward Quantitative Imaging of Soot in an Explosively Generated Fireball.
Abstract not provided.
Saltzman, Ashley↗
Multi-Color Pyrometry of High-speed Ejecta from Pyrotechnic Igniters.
Abstract not provided.
Halls, Benjamin↗
Femtosecond Coherent Anti-Stokes Raman Spectroscopy in a Cold-Flow Hypersonic Wind Tunnel for Simultaneous Pressure and Temperature Measurements.
Abstract not provided.
Richardson, Daniel↗
Development of an Injection-Seeded Tunable OPO for Doppler Global Velocimetry.
Abstract not provided.
Crabtree, Christopher↗
Development of Burst Mode KTP Optical Parametric Oscillator for MHZ PLIF with Extended Burst Durations.
Abstract not provided.
Webb, Austin M↗
Recent Progress in Optical-Based Diagnostics: Applications to Challenging Environments.
Abstract not provided.
Kearney, Sean↗
Pulse-burst spontaneous Raman thermometry of unsteady wave phenomena in a shock tube
A high-speed temperature diagnostic based on spontaneous Raman scattering (SRS) was demonstrated using a pulse-burst laser. The technique was first benchmarked in near-adiabatic H 2 -air flames at a data-acquisition rate of 5 kHz using an integrated pulse energy of 1.0 J per realization. Both the measurement precision and accuracy in the flame were within 3% of adiabatic predictions. Furthermore, this technique was then evaluated in a challenging free-piston shock tube environment operated at a shock Mach number of 3.5. SRS thermometry resolved the temperature in post-incident and post-reflected shock flows at a repetition rate of 3 kHz and clearly showed cooling associated with driver expansion waves. Collectively, this Letter represents a major advancement for SRS in impulsive facilities, which had previously been limited to steady state regions or single-shot acquisition.
47 OTHER INSTRUMENTATION↗