Shock Wave/Transitional Boundary-Layer Interactions in Hypersonic Flow-Reference-Cited by-同舟云学术

Shock Wave/Transitional Boundary-Layer Interactions in Hypersonic Flow

Published:2006-06 Issue:6 Volume:44 Page:1243-1254
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Benay R.¹,Chanetz B.¹,Mangin B.¹,Vandomme L.¹,Perraud J.²

Affiliation:

1. ONERA, 92190 Meudon, France

2. ONERA, 31055 Toulouse, France

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.10512

Reference32 articles.

1. 1Joulot, A. "Contribution à l'Étude de l'Interaction Onde de Choc/ Couche Limite sur Rampe bidimensionnelle en Régime Hypersonique," Ph.D. Dissertation,Univ. Pierreet Marie Curie, Paris,June 1992.

2. Experimental and numerical study of the laminar separation in hypersonic flow

3. 3Chpoun, A. "Contribution à l'Étude d'Écoulements Hypersoniques (M = 5) sur une Rampe de Compression en Configuration 2D et 3D," Ph.D. Dissertation,Univ. Pierreet Marie Curie, Paris,Nov. 1988.

4. 4Heffner, K. "Contribution à l'Étude d'une Rampe de Compression en Écoulement Hypersonique," Ph.D. Dissertation,Univ. Pierreet Marie Curie, Paris,April 1993.

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