Effect of Freestream Noise on Hypersonic Crossflow-Induced Boundary-Layer Transition

Authors

• Andrew Bustard, University of Notre DameFollow
• Thomas J. Juliano, University of Notre Dame
• Harrison B. Yates, Johns Hopkins University Applied Physics Laboratory
• Mark Noftz, Purdue University
• Joseph Jewell, Purdue University

Submitting Campus

Daytona Beach

Department

Aerospace Engineering

Document Type

Article

Publication/Presentation Date

2022

Abstract/Description

Between the windward and leeward rays, boundary-layer transition on cones at angle of attack in hypersonic flow is dominated by the crossflow instability [1, 2], wherein stationary and/or traveling crossflow vortices develop and can breakdown into turbulence [3]. Stationary crossflow modes are caused by surface roughness or any other steady forcing and produce disturbances that are fixed in place on the surface [3–6]. Stationary vortices create a generalized inflection point in the velocity profile that is inviscidly unstable [7]. This distorted mean flow develops secondary instabilities, whose growth and breakdown is one path to turbulence [8–10]. Traveling crossflow modes are caused by freestream noise and/or turbulence, and cause vortical disturbances that convect with the bulk flow [3].

Publication Title

AIAA Journal

DOI

https://doi.org/10.2514/1.J060376

Publisher

American Institute of Aeronautics and Astronautics

Grant or Award Name

Air Force Office of Scientific Research award number FA9550-16-1-0320

Additional Information

Dr. Bustard was not affiliated with Embry-Riddle Aeronautical University at the time this paper was published.

Scholarly Commons Citation

Bustard, A. N., Juliano, T. J., Yates, H. B., Noftz, M., & Jewell, J. S. (2022). Effect of freestream noise on hypersonic crossflow-induced boundary-layer transition. AIAA Journal, 60(12), 6951-6957.