Engineering topics
Lynch, Kyle
Publications and source records attributed to Lynch, Kyle.
Mid-Infrared Laser-Absorption-Spectroscopy Measurements of Temperature, Pressure, and NO at 500 kHz in Shock-Heated Air.
Abstract not provided.
Wall-Modeled Large-Eddy Simulations of Mach 8 Turbulent Boundary Layer and Computation of Aero-Optical Distortions.
Abstract not provided.
Aero-Optical Distortions of Turbulent Boundary Layers: Hypersonic DNS.
Abstract not provided.
Design and Characterization of the Sandia Free-Piston Reflected Shock Tunnel.
Abstract not provided.
Wall-Modeled Large-Eddy Simulations of Mach 8 Turbulent Boundary Layer and Computation of Aero-Optical Distortions.
Abstract not provided.
Burst-mode coherent anti-Stokes Raman scattering thermometry in the Sandia free-piston shock tube.
Abstract not provided.
Mid-Infrared Laser-Absorption-Spectroscopy Measurements of Temperature, Pressure, and NO at 500 kHz in Shock-Heated Air.
Abstract not provided.
Mid-Infrared Laser-Absorption-Spectroscopy Measurements of Temperature, Pressure, and NO at 500 kHz in Shock-Heated Air.
Abstract not provided.
Aero-Optical Distortions of Turbulent Boundary Layers: DNS up to Mach 8.
Abstract not provided.
Scaling of Reflected Shock Bifurcation at High Incident Mach Number.
Abstract not provided.
Development of a Spatially Filtered Wavefront Sensor as an Aero-Optical Measurement Technique .
Abstract not provided.
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.