Plasma-Actuated Flow Control of Hypersonic Crossflow-Induced Boundary-Layer Transition-Reference-Cited by-同舟云学术

Plasma-Actuated Flow Control of Hypersonic Crossflow-Induced Boundary-Layer Transition

Published:2020-05 Issue:5 Volume:58 Page:2093-2108
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Yates Harrison B.¹,Matlis Eric H.¹,Juliano Thomas J.¹,Tufts Matthew W.²

Affiliation:

1. University of Notre Dame, Notre Dame, Indiana 46556-5684

2. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433-7542

Funder

Air Force Office of Scientific Research

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/am-pdf/10.2514/1.J058981

Reference52 articles.

1. STABILITY AND TRANSITION OF THREE-DIMENSIONAL BOUNDARY LAYERS

2. SchueleC. Y. “Control of Stationary Crossflow Modes Using Stationary Patterned Roughness and DBD Plasma Actuators at Mach 3.5,” Ph.D. Thesis, Univ. of Notre Dame, Notre Dame, IN, Sept. 2011.

3. Analysis of Instabilities in Non-Axisymmetric Hypersonic Boundary Layers over Cones

4. Secondary Instabilities of Hypersonic Stationary Crossflow Waves

5. Leading-edge roughness as a transition control mechanism

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