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. This proposal offers an integrated package of truly cutting-edge, high-repetition-rate (up to 1 MHz rate), two-line KTV system for full boundary layer measurement within a single tunnel test. The proposed KTV technique will also avoid any potential model damages. The concepts and ideas proposed are ranging from proof-of-principles demonstration of novel methodologies using a pulse-burst laser pumped two-OPO system for boundary profile measurement in realistic tunnel conditions. The proposed high-repetition-rate KTV technique which is suitable for other flow parameter measurements is a state-of-the-art technique for analysis of unsteady and turbulent flows.
The proposed high-speed burst-mode OPO based two-line KTV technique is suitable for most wind tunnel facilities for full boundary layer velocity profile measurements, including NASA 31” Mach 10 facility, the 11-Foot Transonic Unitary Plan Facility, the Transonic Dynamics Tunnel, and 8- by 6-Foot Supersonic Wind Tunnel, National Transonic Facility (NTF), 0.3-meter Transonic Cryogenic Tunnel (TCT), and NASA HYPULSE Mach 5-25 Shock Tunnel.
The proposed real-time turbulence boundary layer flow tracking system could be applied in many R&D areas, such as gas turbine engines, hypersonic scramjets, hypersonic vehicles, aerospace capsules, and unmanned flights. The potential non-NASA customers could be from research facilities in DoD, DARPA, DOE and other Government agencies and universities.