Stabilization of a nozzle boundary layer by local surface heating
Author:
Affiliation:
1. Montana State University, Bozeman, Montana 59717-0007
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.13429
Reference19 articles.
1. Cooling and roughness effects on transition on nozzle throats and blunt bodies
2. Linear Stability Theory and the Problem of Supersonic Boundary- Layer Transition
3. Comparison of predictions with measurements for a quiet supersonic tunnel
4. Nozzle Wall Boundary-Layer Transition and Freestream Disturbances at Mach 5
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1. Stability of the boundary layer in the Mach-6 contoured nozzle with local surface heating;AIP Conference Proceedings;2021
2. Investigation of the influence of a local change in surface temperature on the laminar boundary layer stability in a hypersonic nozzle;Thermophysics and Aeromechanics;2020-09
3. Initial Flow Quality of the Mach 4 Quiet Ludwieg Tube;AIAA Aviation 2019 Forum;2019-06-14
4. Optimization of a Mach-6 Quiet Wind-Tunnel Nozzle;Journal of Spacecraft and Rockets;2018-03
5. Boundary-Layer Transition Measurements in the Boeing/AFOSR Mach-6 Quiet Tunnel;55th AIAA Aerospace Sciences Meeting;2017-01-05
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