“Supersonic flow” Science-Research, October 2021 — summary from NASA Technology Transfer Program
NASA Technology Transfer Program — summary generated by Brevi Assistant
Researchers at NASA’s Armstrong Flight Research Center and Ames Research Center have created a cutting-edge technique for recording pictures of shock waves emanating from airplane in supersonic flight. NASA has established a unique technique to provide visible density changes in air that create a refractive index change by an airborne vehicle. NASA’s Langley Research Center establishes ingenious modern technologies to control fluid flow in manner ins which will ultimately result in boosted performance and fuel performance. NASA uses two new fluidic oscillator styles that address. Trendsetters at the NASA Langley Research Center have established a system for predicting sonic boom proliferation of supersonic aircraft, the sBOOMTraj tool. SBOOMTraj has possible applications in the style and advancement of future generation supersonic aircraft, and might also allow pilots and operators of such airplane to plan flight paths to reduce their noise footprints. NASA’s Langley Research Center has established a technology that is forecasted to extend the laminar flow area over supersonic trip setups by postponing the shift of limit layer flow from laminar to unstable state. It can be used in combination with most of the existing methods for passive and active laminar flow control, yet is particularly well-suited for a supersonic all-natural laminar flow design by virtue of preventing the space, weight, system intricacy, and maintenance fines connected with suction based laminar flow control. Standard second-throat and round diffusers permit supersonic gas streams to expand within their walls and pull a vacuum cleaner on any type of upstream space. A new sort of spike diffuser recently established by NASA Stennis Space Center is able to provide approximately double the pumping performance of second-throat diffusers through Pareto-efficient reduction of both core Mach number and flow deflection.
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