Modal Analysis of Cylinder-Induced Transitional Shock-Wave/Boundary-Layer Interaction Unsteadiness-Reference-Cited by-同舟云学术

Modal Analysis of Cylinder-Induced Transitional Shock-Wave/Boundary-Layer Interaction Unsteadiness

Published:2022-05 Issue:5 Volume:60 Page:2730-2748
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Hoffman Eugene N. A.,Rodriguez Jose M.,Cottier Stephanie M.,Combs Christopher S.,Bathel Brett F.,Weisberger Joshua M.,Jones Stephen B.¹,Schmisseur John D.,Kreth Phillip A.

Affiliation:

1. Analytical Mechanics Associates, Inc., Hampton, Virginia 23681

Funder

NASA

Langley Research Center

Office of Naval Research

Air Force Office of Scientific Research

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.J060880

Reference38 articles.

1. BabinskyH.HarveyJ. K., Shock Wave–Boundary-Layer Interactions, Cambridge Univ. Press, Cambridge, New York, 2011, p. 1.

2. JenkinsD. R., Hypersonics Before the Shuttle: A Concise History of the X-15 Research Airplane, NASA Office of Policy and Plans, 2000, p. 54, Chap. 3.

3. Fifty Years of Shock-Wave/Boundary-Layer Interaction Research: What Next?

4. KnightD. D.DegrezG. “Shock Wave Boundary Layer Interactions in High Mach Number Flows a Critical Survey of Current Numerical Prediction Capabilities,” AGARD Advisory Report Agard Ar., Tech. Rept. AR-319, Vol. 2, 1998.

5. SettlesG. S.DodsonL. J. “Hypersonic Shock/Boundary-Layer Interaction Database: New and Corrected Data,” Pennsylvania State Univ., NASA CR 177638, 1994. 10.2514/6.1991-1763

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