High-Repetition-Rate, Two-Line Kr Tagging Velocimetry for Full Boundary Layer Velocity Profile Measurement in a Single Tunnel Test

NASA aero-science ground test facilities, including transonic, supersonic and hypersonic wind tunnels, provide critical data and fundamental insight required to understand complex phenomena and support the advancement of computational tools for modeling and simulation. In these facilities, high-repetition-rate (10 kHz–1 MHz) full boundary layer velocity profile measurement techniques are needed to track the turbulent boundary layer dynamics. Current state-of-the-art boundary measurement capabilities are really limited because of intrusiveness, model surface damaging with high-peak laser intensity, experimental complexity (e.g., need holes on the model), high measurement uncertainty, and low spatiotemporal resolution. This proposal offers an integrated package of truly cutting-edge, high-repetition-rate (up to 1 MHz rate), single-line or two-line KTV system for full boundary layer velocity profile measurement within a single tunnel test. The proposed KTV technique provides high accuracy with high spatiotemporal resolution and will also avoid any potential model damages – enabling measurement everywhere on the model. The concepts and ideas proposed are ranging from proof-of-principles demonstration of novel methodologies using a pulse-burst laser pumped Kr-OPO system for boundary profile measurement to applications realistic tunnel conditions. The proposed high-repetition-rate KTV system can be also used for Kr-PLIF imaging, providing flow structure and other flow parameters information for understanding of unsteady and turbulent flows, particularly in boundary layers.

The proposed research effort will provide new instrumentation capabilities and methodologies, together with a convenient and user-friendly software package for the high-speed KTV system control, data analysis and interpretation, for tracking turbulent boundary layer that is required as inputs to model and predict complicated turbulence flow behavior in NASA large-scale wind tunnels. The proposed system developed under this SBIR work will help to reduce programmatic risk for the high-speed Test and Evaluation (T&E) community.

This system could also be applied in various large test facilities in many universities, research institutes and aviation companies for accurate flow and combustion measurements. The potential customers could be from research facilities in DoD, DARPA, DOE and other Government agencies, industrial aeronautical companies, such asBoeing, Lockheed Martin, GE, Pratt-Whitney, and Raytheon.

This is early/mid-stage (TRL 6) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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