Design of a Hypersonic Boundary Layer Transition Control Experiment Utilizing a Swept Fin Cone Geometry in Mach 6 Flow
Author:
Affiliation:
1. University of Notre Dame
2. Texas A&M University
Publisher
American Institute of Aeronautics and Astronautics
Reference33 articles.
1. X-43A Hypersonic vehicle technology development
2. CRITICAL HYPERSONIC AEROTHERMODYNAMIC PHENOMENA
3. Effects of Roughness on Hypersonic Boundary-Layer Transition
4. Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics
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1. Crossflow Instability on a Swept Fin–Cone with Variable Nose Bluntness in Mach 6 Flow;AIAA Journal;2024-06
2. Boundary-layer instability on a highly swept fin on a cone at Mach 6;Journal of Fluid Mechanics;2024-05-16
3. Numerical study of discrete film cooling near the rudder shaft of a hypersonic air fin model;Numerical Heat Transfer, Part A: Applications;2023-04-03
4. Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control;Plasma Science and Technology;2022-07-20
5. A wrap-film technique for infrared thermography heat-transfer measurements in high-speed wind tunnels;Experimental Thermal and Fluid Science;2022-07
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