Boundary-Layer Instabilities over a Cone–Cylinder–Flare Model at Mach 6-Reference-Cited by-同舟云学术

Boundary-Layer Instabilities over a Cone–Cylinder–Flare Model at Mach 6

Published:2022-10 Issue:10 Volume:60 Page:5652-5661
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Paredes Pedro¹^ORCID,Scholten Anton²^ORCID,Choudhari Meelan M.³,Li Fei³,Benitez Elizabeth K.⁴^ORCID,Jewell Joseph S.⁵

Affiliation:

1. National Institute of Aerospace, Hampton, Virginia 23666

2. North Carolina State University, Raleigh, North Carolina 27695

3. NASA Langley Research Center, Hampton, Virginia 23681

4. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433

5. Purdue University, West Lafayette, Indiana 47907

Funder

Office of Naval Research Global

Aeronautics Research Mission Directorate

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.J061829

Reference45 articles.

1. BeckerJ.KorycinskyP. “Heat Transfer and Pressure Distribution at a Mach Number of 6.7 on Bodies with Conical Flares and Extensive Flow Separation,” NACA RM L56F22, NACA, 1956.

2. ChapmanD.KuehnD.LarsonH. “Investigation of Separated Flows in Supersonic and Subsonic Streams with Emphasis of the Effect of Transition,” NACA TR 1356, NACA, 1958.

3. Investigation of Separation and Associated Heat Transfer and Pressure Distribution on Cone-Cylinder-Flare Configurations at Mach Five

4. Hypersonic shock-wave/boundary-layer interactions on a cone/flare

5. GinouxJ. “Investigation of Flow Separation over Ramps at M∞=3,” Von Karman Gas Dynamics Facility, TR AEDC-TR-65-273, Arnold Engineering Development Center, 1965.

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