Freestream Disturbances Characterization in Ludwieg Tubes at Mach 6
The present study aims at freestream disturbances characterization for two hypersonic sister facilities; HLB of the TU Braunschweig and HHK-6 of the USAF Academy. The freestream disturbances are characterized by using a so-called combined modal analysis. For this analysis, measurements are taken by means of hotwire and stagnation point probes. Although both facilities utilize the same nozzle geometry, they have different storage tubes. The present results provide insight into current methods used to characterize freestream disturbances in hypersonic flow. Further assessment is possible by comparisons with recent data from direct numerical simulation of the noise radiated from the hypersonic turbulent boundary layer of the wind tunnel nozzle.
F. Munoz et al., "Freestream Disturbances Characterization in Ludwieg Tubes at Mach 6," Proceedings of the AIAA Scitech 2019 Forum (2019, San Diego, CA), American Institute of Aeronautics and Astronautics (AIAA), Jan 2019.
The definitive version is available at https://doi.org/10.2514/6.2019-0878
AIAA Scitech Forum, 2019 (2019: Jan. 7-11, San Diego, CA)
Mechanical and Aerospace Engineering
Keywords and Phrases
Aviation; Boundary layer flow; Digital storage; Hypersonic flow; Modal analysis; Nozzles; Wind tunnels, Free-stream; Hotwire; Ludwieg tube; Nozzle geometries; Stagnation points; Turbulent boundary layers, Hypersonic boundary layers
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2019 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 2019